Appendix I - Tables of Profiles

Public Domain Aeronautical Software (PDAS)

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Four digit profiles
0006 0008 0010 0012 0015 0018 0021

Modified four digit profiles
0008-34 0010-34 0010-35 0010-64 0010-65 0010-66 0012-34 0012-64

16-series profiles
16-006 16-009 16-012 16-015 16-018 16-021

63 series profiles
63-006 63-008 63-009 63-010
63-012 63-015 63-018 63-021

63A series profiles
63A-006 63A-000 63A-010 63A-012 63A-015

64 series profiles
64-006 64-008 64-009 64-010
64-012 64-015 64-018 64-021

64A series profiles
64A-006 64A-008 64A-010 64A-012 64A-015

65 series profiles
65-006 65-008 65-009 65-010
65-012 65-015 65-018 65-021

65A series profiles
65A-006 65A-008 65A-010 65A-012 65A-015

66 series profiles
66-006 66-008 66-009 66-010
66-012 66-015 66-018 66-021

67 series profiles
67-012 67-015

NACA Profile 0006
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.6107	0.5910
0.7500	0.7424	0.4749
1.2500	0.9470	0.3579
2.5000	1.3074	0.2387
5.0000	1.7773	0.1514
7.5000	2.1000	0.1104
10.0000	2.3414	0.0844
15.0000	2.6726	0.0509
20.0000	2.8688	0.0289
25.0000	2.9706	0.0126
30.0000	3.0009	-0.0000
35.0000	2.9743	-0.0102
40.0000	2.9015	-0.0186
45.0000	2.7904	-0.0256
50.0000	2.6470	-0.0316
55.0000	2.4762	-0.0366
60.0000	2.2817	-0.0411
65.0000	2.0662	-0.0450
70.0000	1.8320	-0.0486
75.0000	1.5802	-0.0521
80.0000	1.3116	-0.0554
85.0000	1.0263	-0.0587
90.0000	0.7239	-0.0623
95.0000	0.4033	-0.0660
100.0000	0.0630	-0.0702
L.E. radius = 0.397 percent chord

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NACA Profile 0008
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.8142	0.7880
0.7500	0.9899	0.6332
1.2500	1.2626	0.4772
2.5000	1.7431	0.3183
5.0000	2.3698	0.2019
7.5000	2.7999	0.1472
10.0000	3.1218	0.1125
15.0000	3.5634	0.0679
20.0000	3.8250	0.0385
25.0000	3.9608	0.0168
30.0000	4.0012	-0.0001
35.0000	3.9657	-0.0136
40.0000	3.8687	-0.0248
45.0000	3.7205	-0.0342
50.0000	3.5294	-0.0421
55.0000	3.3016	-0.0489
60.0000	3.0422	-0.0548
65.0000	2.7550	-0.0600
70.0000	2.4426	-0.0649
75.0000	2.1069	-0.0694
80.0000	1.7487	-0.0738
85.0000	1.3684	-0.0783
90.0000	0.9651	-0.0830
95.0000	0.5377	-0.0880
100.0000	0.0840	-0.0935
L.E. radius = 0.705 percent chord

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NACA Profile 0010
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	1.0178	0.9850
0.7500	1.2374	0.7915
1.2500	1.5783	0.5966
2.5000	2.1789	0.3979
5.0000	2.9622	0.2524
7.5000	3.4999	0.1840
10.0000	3.9023	0.1406
15.0000	4.4543	0.0848
20.0000	4.7813	0.0481
25.0000	4.9510	0.0210
30.0000	5.0014	-0.0001
35.0000	4.9572	-0.0171
40.0000	4.8358	-0.0310
45.0000	4.6506	-0.0427
50.0000	4.4117	-0.0526
55.0000	4.1270	-0.0611
60.0000	3.8028	-0.0685
65.0000	3.4437	-0.0750
70.0000	3.0533	-0.0811
75.0000	2.6336	-0.0868
80.0000	2.1859	-0.0923
85.0000	1.7105	-0.0979
90.0000	1.2064	-0.1038
95.0000	0.6721	-0.1100
100.0000	0.1050	-0.1169
L.E. radius = 1.102 percent chord

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NACA Profile 0012
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	1.2213	1.1819
0.7500	1.4849	0.9498
1.2500	1.8939	0.7159
2.5000	2.6147	0.4775
5.0000	3.5547	0.3029
7.5000	4.1999	0.2208
10.0000	4.6828	0.1687
15.0000	5.3452	0.1018
20.0000	5.7375	0.0577
25.0000	5.9412	0.0252
30.0000	6.0017	-0.0001
35.0000	5.9486	-0.0205
40.0000	5.8030	-0.0372
45.0000	5.5807	-0.0513
50.0000	5.2940	-0.0631
55.0000	4.9524	-0.0733
60.0000	4.5634	-0.0822
65.0000	4.1325	-0.0901
70.0000	3.6639	-0.0973
75.0000	3.1603	-0.1041
80.0000	2.6231	-0.1108
85.0000	2.0526	-0.1175
90.0000	1.4477	-0.1245
95.0000	0.8066	-0.1321
100.0000	0.1260	-0.1403
L.E. radius = 1.587 percent chord

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NACA Profile 0015
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	1.5266	1.4774
0.7500	1.8561	1.1872
1.2500	2.3674	0.8948
2.5000	3.2684	0.5969
5.0000	4.4434	0.3786
7.5000	5.2499	0.2760
10.0000	5.8535	0.2109
15.0000	6.6815	0.1272
20.0000	7.1719	0.0721
25.0000	7.4266	0.0315
30.0000	7.5022	-0.0001
35.0000	7.4358	-0.0256
40.0000	7.2538	-0.0466
45.0000	6.9759	-0.0641
50.0000	6.6175	-0.0789
55.0000	6.1905	-0.0916
60.0000	5.7042	-0.1027
65.0000	5.1656	-0.1126
70.0000	4.5799	-0.1216
75.0000	3.9504	-0.1301
80.0000	3.2789	-0.1385
85.0000	2.5657	-0.1469
90.0000	1.8096	-0.1556
95.0000	1.0082	-0.1651
100.0000	0.1575	-0.1754
L.E. radius = 2.479 percent chord

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NACA Profile 0018
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	1.8320	1.7729
0.7500	2.2273	1.4246
1.2500	2.8409	1.0738
2.5000	3.9221	0.7162
5.0000	5.3320	0.4543
7.5000	6.2999	0.3312
10.0000	7.0242	0.2531
15.0000	8.0177	0.1527
20.0000	8.6063	0.0866
25.0000	8.9119	0.0379
30.0000	9.0026	-0.0001
35.0000	8.9229	-0.0307
40.0000	8.7045	-0.0559
45.0000	8.3711	-0.0769
50.0000	7.9410	-0.0947
55.0000	7.4286	-0.1099
60.0000	6.8451	-0.1232
65.0000	6.1987	-0.1351
70.0000	5.4959	-0.1459
75.0000	4.7405	-0.1562
80.0000	3.9347	-0.1661
85.0000	3.0788	-0.1762
90.0000	2.1716	-0.1868
95.0000	1.2098	-0.1981
100.0000	0.1890	-0.2105
L.E. radius = 3.570 percent chord

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NACA Profile 0021
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	2.1373	2.0684
0.7500	2.5985	1.6621
1.2500	3.3143	1.2528
2.5000	4.5758	0.8356
5.0000	6.2207	0.5301
7.5000	7.3498	0.3863
10.0000	8.1948	0.2953
15.0000	9.3540	0.1781
20.0000	10.0407	0.1010
25.0000	10.3972	0.0442
30.0000	10.5030	-0.0001
35.0000	10.4101	-0.0358
40.0000	10.1553	-0.0652
45.0000	9.7663	-0.0897
50.0000	9.2645	-0.1104
55.0000	8.6667	-0.1282
60.0000	7.9859	-0.1438
65.0000	7.2319	-0.1576
70.0000	6.4118	-0.1703
75.0000	5.5305	-0.1822
80.0000	4.5905	-0.1938
85.0000	3.5920	-0.2056
90.0000	2.5335	-0.2179
95.0000	1.4115	-0.2311
100.0000	0.2205	-0.2455
L.E. radius = 4.859 percent chord

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NACA Profile 0008-34
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.4578	0.4946
0.7500	0.5707	0.4164
1.2500	0.7566	0.3370
2.5000	1.1174	0.2538
5.0000	1.6583	0.1884
7.5000	2.0830	0.1540
10.0000	2.4364	0.1298
15.0000	2.9926	0.0947
20.0000	3.3969	0.0681
25.0000	3.6815	0.0464
30.0000	3.8669	0.0283
35.0000	3.9687	0.0129
40.0000	4.0000	0.0000
45.0000	3.9708	0.0117
50.0000	3.8838	0.0231
55.0000	3.7401	0.0343
60.0000	3.5409	0.0453
65.0000	3.2873	0.0561
70.0000	2.9803	0.0667
75.0000	2.6211	0.0770
80.0000	2.2107	0.0871
85.0000	1.7503	0.0970
90.0000	1.2410	0.1067
95.0000	0.6839	0.1161
100.0000	0.0800	0.1254
L.E. radius = 0.176 percent chord

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NACA Profile 0010-34
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.5722	0.6182
0.7500	0.7133	0.5205
1.2500	0.9457	0.4212
2.5000	1.3968	0.3173
5.0000	2.0728	0.2355
7.5000	2.6038	0.1925
10.0000	3.0455	0.1623
15.0000	3.7408	0.1183
20.0000	4.2461	0.0851
25.0000	4.6018	0.0580
30.0000	4.8336	0.0353
35.0000	4.9609	0.0161
40.0000	5.0000	0.0000
45.0000	4.9634	0.0146
50.0000	4.8547	0.0289
55.0000	4.6751	0.0429
60.0000	4.4261	0.0567
65.0000	4.1091	0.0701
70.0000	3.7254	0.0833
75.0000	3.2764	0.0962
80.0000	2.7634	0.1089
85.0000	2.1879	0.1213
90.0000	1.5513	0.1334
95.0000	0.8548	0.1452
100.0000	0.1000	0.1567
L.E. radius = 0.275 percent chord

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NACA Profile 0010-35
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.5457	0.5660
0.7500	0.6739	0.4692
1.2500	0.8810	0.3717
2.5000	1.2730	0.2722
5.0000	1.8469	0.1987
7.5000	2.2960	0.1636
10.0000	2.6748	0.1408
15.0000	3.2958	0.1098
20.0000	3.7870	0.0876
25.0000	4.1782	0.0694
30.0000	4.4844	0.0534
35.0000	4.7148	0.0389
40.0000	4.8750	0.0253
45.0000	4.9691	0.0124
50.0000	5.0000	0.0000
55.0000	4.9676	0.0133
60.0000	4.8631	0.0289
65.0000	4.6753	0.0466
70.0000	4.3932	0.0666
75.0000	4.0057	0.0888
80.0000	3.5018	0.1132
85.0000	2.8703	0.1398
90.0000	2.1003	0.1686
95.0000	1.1805	0.1997
100.0000	0.1000	0.2329
L.E. radius = 0.275 percent chord

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NACA Profile 0010-64
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.9880	0.9266
0.7500	1.1932	0.7345
1.2500	1.5062	0.5421
2.5000	2.0428	0.3497
5.0000	2.7205	0.2160
7.5000	3.1808	0.1583
10.0000	3.5315	0.1247
15.0000	4.0471	0.0855
20.0000	4.4115	0.0617
25.0000	4.6742	0.0440
30.0000	4.8556	0.0288
35.0000	4.9637	0.0145
40.0000	5.0000	0.0000
45.0000	4.9634	0.0146
50.0000	4.8547	0.0289
55.0000	4.6751	0.0429
60.0000	4.4261	0.0567
65.0000	4.1091	0.0701
70.0000	3.7254	0.0833
75.0000	3.2764	0.0962
80.0000	2.7634	0.1089
85.0000	2.1879	0.1213
90.0000	1.5513	0.1334
95.0000	0.8548	0.1452
100.0000	0.1000	0.1567
L.E. radius = 1.102 percent chord

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NACA Profile 0010-65
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.9728	0.8967
0.7500	1.1705	0.7049
1.2500	1.4690	0.5133
2.5000	1.9707	0.3229
5.0000	2.5862	0.1929
7.5000	2.9935	0.1390
10.0000	3.3005	0.1091
15.0000	3.7556	0.0769
20.0000	4.0938	0.0598
25.0000	4.3631	0.0485
30.0000	4.5820	0.0393
35.0000	4.7569	0.0306
40.0000	4.8877	0.0215
45.0000	4.9707	0.0115
50.0000	5.0000	0.0000
55.0000	4.9676	0.0133
60.0000	4.8631	0.0289
65.0000	4.6753	0.0466
70.0000	4.3932	0.0666
75.0000	4.0057	0.0888
80.0000	3.5018	0.1132
85.0000	2.8703	0.1398
90.0000	2.1003	0.1686
95.0000	1.1805	0.1997
100.0000	0.1000	0.2329
L.E. radius = 1.102 percent chord

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NACA Profile 0010-66
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.9820	0.9147
0.7500	1.1842	0.7224
1.2500	1.4912	0.5299
2.5000	2.0123	0.3372
5.0000	2.6580	0.2030
7.5000	3.0855	0.1452
10.0000	3.4036	0.1119
15.0000	3.8584	0.0743
20.0000	4.1735	0.0535
25.0000	4.4056	0.0402
30.0000	4.5823	0.0309
35.0000	4.7186	0.0239
40.0000	4.8234	0.0182
45.0000	4.9017	0.0132
50.0000	4.9565	0.0087
55.0000	4.9891	0.0044
60.0000	5.0000	-0.0000
65.0000	4.9808	0.0093
70.0000	4.8905	0.0285
75.0000	4.6798	0.0575
80.0000	4.2996	0.0963
85.0000	3.7007	0.1449
90.0000	2.8339	0.2034
95.0000	1.6501	0.2717
100.0000	0.1000	0.3499
L.E. radius = 1.102 percent chord

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NACA Profile 0012-34
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.6867	0.7418
0.7500	0.8560	0.6246
1.2500	1.1348	0.5054
2.5000	1.6761	0.3807
5.0000	2.4874	0.2825
7.5000	3.1245	0.2310
10.0000	3.6546	0.1948
15.0000	4.4889	0.1420
20.0000	5.0953	0.1021
25.0000	5.5222	0.0696
30.0000	5.8003	0.0424
35.0000	5.9530	0.0194
40.0000	6.0000	0.0000
45.0000	5.9561	0.0175
50.0000	5.8256	0.0347
55.0000	5.6102	0.0515
60.0000	5.3114	0.0680
65.0000	4.9309	0.0841
70.0000	4.4704	0.1000
75.0000	3.9316	0.1155
80.0000	3.3161	0.1307
85.0000	2.6255	0.1455
90.0000	1.8615	0.1600
95.0000	1.0258	0.1742
100.0000	0.1200	0.1881
L.E. radius = 0.397 percent chord

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NACA Profile 0012-64
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	1.1855	1.1120
0.7500	1.4318	0.8813
1.2500	1.8074	0.6506
2.5000	2.4513	0.4197
5.0000	3.2647	0.2592
7.5000	3.8170	0.1900
10.0000	4.2378	0.1497
15.0000	4.8565	0.1027
20.0000	5.2938	0.0741
25.0000	5.6091	0.0528
30.0000	5.8267	0.0346
35.0000	5.9564	0.0173
40.0000	6.0000	0.0000
45.0000	5.9561	0.0175
50.0000	5.8256	0.0347
55.0000	5.6102	0.0515
60.0000	5.3114	0.0680
65.0000	4.9309	0.0841
70.0000	4.4704	0.1000
75.0000	3.9316	0.1155
80.0000	3.3161	0.1307
85.0000	2.6255	0.1455
90.0000	1.8615	0.1600
95.0000	1.0258	0.1742
100.0000	0.1200	0.1881
L.E. radius = 1.587 percent chord

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NACA Profile 16-006
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.4128	0.4057
0.7500	0.5037	0.3287
1.2500	0.6462	0.2514
2.5000	0.9034	0.1734
5.0000	1.2560	0.1181
7.5000	1.5171	0.0932
10.0000	1.7300	0.0781
15.0000	2.0694	0.0593
20.0000	2.3336	0.0470
25.0000	2.5439	0.0374
30.0000	2.7102	0.0292
35.0000	2.8373	0.0217
40.0000	2.9276	0.0144
45.0000	2.9818	0.0073
50.0000	3.0000	0.0000
55.0000	2.9806	0.0080
60.0000	2.9178	0.0173
65.0000	2.8052	0.0280
70.0000	2.6359	0.0400
75.0000	2.4034	0.0533
80.0000	2.1011	0.0679
85.0000	1.7222	0.0839
90.0000	1.2602	0.1012
95.0000	0.7083	0.1198
100.0000	0.0600	0.1398
L.E. radius = 0.176 percent chord

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NACA Profile 16-009
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.6192	0.6086
0.7500	0.7555	0.4930
1.2500	0.9693	0.3770
2.5000	1.3550	0.2602
5.0000	1.8840	0.1771
7.5000	2.2756	0.1399
10.0000	2.5950	0.1172
15.0000	3.1042	0.0890
20.0000	3.5004	0.0705
25.0000	3.8158	0.0562
30.0000	4.0653	0.0438
35.0000	4.2559	0.0325
40.0000	4.3913	0.0217
45.0000	4.4727	0.0109
50.0000	4.5000	0.0000
55.0000	4.4709	0.0120
60.0000	4.3768	0.0260
65.0000	4.2078	0.0420
70.0000	3.9539	0.0599
75.0000	3.6052	0.0799
80.0000	3.1516	0.1019
85.0000	2.5833	0.1258
90.0000	1.8902	0.1518
95.0000	1.0625	0.1797
100.0000	0.0900	0.2096
L.E. radius = 0.397 percent chord

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NACA Profile 16-012
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.8256	0.8115
0.7500	1.0073	0.6573
1.2500	1.2924	0.5027
2.5000	1.8067	0.3469
5.0000	2.5120	0.2362
7.5000	3.0342	0.1865
10.0000	3.4600	0.1562
15.0000	4.1389	0.1186
20.0000	4.6671	0.0940
25.0000	5.0878	0.0749
30.0000	5.4203	0.0585
35.0000	5.6746	0.0434
40.0000	5.8551	0.0289
45.0000	5.9636	0.0145
50.0000	6.0000	0.0000
55.0000	5.9611	0.0160
60.0000	5.8357	0.0346
65.0000	5.6103	0.0559
70.0000	5.2718	0.0799
75.0000	4.8069	0.1065
80.0000	4.2022	0.1358
85.0000	3.4444	0.1677
90.0000	2.5203	0.2023
95.0000	1.4166	0.2396
100.0000	0.1200	0.2795
L.E. radius = 0.705 percent chord

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NACA Profile 16-015
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	1.0321	1.0144
0.7500	1.2591	0.8217
1.2500	1.6155	0.6284
2.5000	2.2584	0.4336
5.0000	3.1400	0.2952
7.5000	3.7927	0.2331
10.0000	4.3250	0.1953
15.0000	5.1736	0.1483
20.0000	5.8339	0.1175
25.0000	6.3597	0.0936
30.0000	6.7754	0.0731
35.0000	7.0932	0.0542
40.0000	7.3189	0.0361
45.0000	7.4545	0.0181
50.0000	7.5000	0.0000
55.0000	7.4514	0.0200
60.0000	7.2946	0.0433
65.0000	7.0129	0.0699
70.0000	6.5898	0.0999
75.0000	6.0086	0.1332
80.0000	5.2527	0.1698
85.0000	4.3055	0.2097
90.0000	3.1504	0.2529
95.0000	1.7708	0.2995
100.0000	0.1500	0.3494
L.E. radius = 1.102 percent chord

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NACA Profile 16-018
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	1.2385	1.2172
0.7500	1.5110	0.9860
1.2500	1.9386	0.7541
2.5000	2.7101	0.5203
5.0000	3.7680	0.3542
7.5000	4.5513	0.2797
10.0000	5.1900	0.2343
15.0000	6.2083	0.1780
20.0000	7.0007	0.1410
25.0000	7.6316	0.1123
30.0000	8.1305	0.0877
35.0000	8.5119	0.0651
40.0000	8.7827	0.0433
45.0000	8.9454	0.0218
50.0000	9.0000	0.0000
55.0000	8.9417	0.0240
60.0000	8.7535	0.0520
65.0000	8.4155	0.0839
70.0000	7.9078	0.1199
75.0000	7.2103	0.1598
80.0000	6.3033	0.2037
85.0000	5.1666	0.2516
90.0000	3.7805	0.3035
95.0000	2.1249	0.3594
100.0000	0.1800	0.4193
L.E. radius = 1.587 percent chord

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NACA Profile 16-021
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	1.4449	1.4201
0.7500	1.7628	1.1503
1.2500	2.2617	0.8797
2.5000	3.1618	0.6070
5.0000	4.3960	0.4133
7.5000	5.3098	0.3263
10.0000	6.0550	0.2734
15.0000	7.2430	0.2076
20.0000	8.1675	0.1645
25.0000	8.9036	0.1310
30.0000	9.4856	0.1023
35.0000	9.9305	0.0759
40.0000	10.2464	0.0505
45.0000	10.4363	0.0254
50.0000	10.5000	0.0000
55.0000	10.4320	0.0280
60.0000	10.2124	0.0606
65.0000	9.8181	0.0979
70.0000	9.2257	0.1398
75.0000	8.4120	0.1864
80.0000	7.3538	0.2377
85.0000	6.0277	0.2935
90.0000	4.4106	0.3541
95.0000	2.4791	0.4193
100.0000	0.2100	0.4891
L.E. radius = 2.160 percent chord

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NACA Profile 63-006
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	0.5039	0.4762
0.7500	0.6093	0.3777
1.2500	0.7709	0.2809
2.5000	1.0568	0.1945
5.0000	1.4626	0.1383
7.5000	1.7666	0.1077
10.0000	2.0107	0.0890
15.0000	2.3872	0.0638
20.0000	2.6572	0.0451
25.0000	2.8424	0.0294
30.0000	2.9558	0.0154
35.0000	2.9990	0.0013
40.0000	2.9712	-0.0124
45.0000	2.8764	-0.0253
50.0000	2.7218	-0.0364
55.0000	2.5161	-0.0456
60.0000	2.2679	-0.0536
65.0000	1.9844	-0.0599
70.0000	1.6727	-0.0646
75.0000	1.3433	-0.0672
80.0000	1.0075	-0.0671
85.0000	0.6806	-0.0633
90.0000	0.3820	-0.0555
95.0000	0.1371	-0.0405
100.0000	-0.0000	-0.0008
L.E. radius = 0.268 percent chord

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NACA Profile 63-008
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	0.6682	0.6340
0.7500	0.8087	0.5036
1.2500	1.0244	0.3755
2.5000	1.4073	0.2609
5.0000	1.9516	0.1854
7.5000	2.3588	0.1442
10.0000	2.6857	0.1191
15.0000	3.1895	0.0852
20.0000	3.5500	0.0599
25.0000	3.7964	0.0391
30.0000	3.9458	0.0201
35.0000	3.9998	0.0007
40.0000	3.9577	-0.0176
45.0000	3.8252	-0.0351
50.0000	3.6131	-0.0498
55.0000	3.3336	-0.0618
60.0000	2.9982	-0.0722
65.0000	2.6172	-0.0802
70.0000	2.2003	-0.0858
75.0000	1.7616	-0.0891
80.0000	1.3171	-0.0882
85.0000	0.8871	-0.0830
90.0000	0.4963	-0.0725
95.0000	0.1777	-0.0529
100.0000	0.0000	-0.0011
L.E. radius = 0.471 percent chord

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NACA Profile 63-009
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	0.7490	0.7124
0.7500	0.9070	0.5665
1.2500	1.1497	0.4230
2.5000	1.5815	0.2944
5.0000	2.1958	0.2092
7.5000	2.6550	0.1627
10.0000	3.0237	0.1343
15.0000	3.5915	0.0959
20.0000	3.9974	0.0673
25.0000	4.2743	0.0439
30.0000	4.4414	0.0225
35.0000	4.5001	0.0005
40.0000	4.4499	-0.0204
45.0000	4.2974	-0.0401
50.0000	4.0556	-0.0565
55.0000	3.7383	-0.0701
60.0000	3.3586	-0.0810
65.0000	2.9282	-0.0904
70.0000	2.4585	-0.0966
75.0000	1.9654	-0.0997
80.0000	1.4673	-0.0985
85.0000	0.9867	-0.0925
90.0000	0.5512	-0.0806
95.0000	0.1971	-0.0589
100.0000	0.0000	-0.0012
L.E. radius = 0.590 percent chord

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NACA Profile 63-010
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.8286	0.7905
0.7500	1.0040	0.6293
1.2500	1.2739	0.4706
2.5000	1.7548	0.3281
5.0000	2.4396	0.2332
7.5000	2.9512	0.1812
10.0000	3.3619	0.1494
15.0000	3.9941	0.1066
20.0000	4.4454	0.0748
25.0000	4.7529	0.0488
30.0000	4.9374	0.0249
35.0000	5.0003	0.0003
40.0000	4.9414	-0.0233
45.0000	4.7682	-0.0452
50.0000	4.4959	-0.0634
55.0000	4.1401	-0.0784
60.0000	3.7158	-0.0903
65.0000	3.2357	-0.1007
70.0000	2.7131	-0.1074
75.0000	2.1659	-0.1101
80.0000	1.6146	-0.1088
85.0000	1.0841	-0.1018
90.0000	0.6047	-0.0884
95.0000	0.2160	-0.0648
100.0000	-0.0000	-0.0013
L.E. radius = 0.719 percent chord

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NACA Profile 63-012
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.9838	0.9453
0.7500	1.1938	0.7547
1.2500	1.5181	0.5663
2.5000	2.0979	0.3964
5.0000	2.9256	0.2817
7.5000	3.5432	0.2186
10.0000	4.0386	0.1800
15.0000	4.8003	0.1280
20.0000	5.3431	0.0899
25.0000	5.7115	0.0585
30.0000	5.9304	0.0295
35.0000	6.0005	-0.0008
40.0000	5.9220	-0.0299
45.0000	5.7051	-0.0557
50.0000	5.3698	-0.0777
55.0000	4.9354	-0.0957
60.0000	4.4206	-0.1100
65.0000	3.8398	-0.1220
70.0000	3.2112	-0.1294
75.0000	2.5567	-0.1319
80.0000	1.9002	-0.1298
85.0000	1.2724	-0.1201
90.0000	0.7076	-0.1038
95.0000	0.2521	-0.0759
100.0000	-0.0000	-0.0016
L.E. radius = 1.004 percent chord

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NACA Profile 63-015
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	1.2039	1.1731
0.7500	1.4654	0.9415
1.2500	1.8712	0.7107
2.5000	2.6018	0.5010
5.0000	3.6488	0.3561
7.5000	4.4285	0.2757
10.0000	5.0532	0.2266
15.0000	6.0121	0.1606
20.0000	6.6934	0.1128
25.0000	7.1533	0.0728
30.0000	7.4222	0.0348
35.0000	7.4992	-0.0039
40.0000	7.3860	-0.0416
45.0000	7.0988	-0.0733
50.0000	6.6640	-0.0996
55.0000	6.1072	-0.1219
60.0000	5.4529	-0.1398
65.0000	4.7194	-0.1530
70.0000	3.9318	-0.1606
75.0000	3.1176	-0.1636
80.0000	2.3073	-0.1597
85.0000	1.5389	-0.1474
90.0000	0.8524	-0.1262
95.0000	0.3026	-0.0912
100.0000	0.0000	-0.0019
L.E. radius = 1.472 percent chord

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NACA Profile 63-018
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	1.4050	1.3929
0.7500	1.7166	1.1258
1.2500	2.2041	0.8562
2.5000	3.0883	0.6086
5.0000	4.3620	0.4329
7.5000	5.3086	0.3344
10.0000	6.0657	0.2743
15.0000	7.2259	0.1941
20.0000	8.0478	0.1360
25.0000	8.5992	0.0864
30.0000	8.9162	0.0397
35.0000	8.9961	-0.0075
40.0000	8.8419	-0.0525
45.0000	8.4783	-0.0911
50.0000	7.9382	-0.1241
55.0000	7.2546	-0.1488
60.0000	6.4567	-0.1693
65.0000	5.5689	-0.1843
70.0000	4.6226	-0.1935
75.0000	3.6506	-0.1945
80.0000	2.6909	-0.1873
85.0000	1.7880	-0.1713
90.0000	0.9866	-0.1464
95.0000	0.3492	-0.1050
100.0000	0.0000	-0.0023
L.E. radius = 1.951 percent chord

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NACA Profile 63-021
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	1.5829	1.6012
0.7500	1.9430	1.3061
1.2500	2.5116	1.0024
2.5000	3.5525	0.7196
5.0000	5.0615	0.5129
7.5000	6.1810	0.3948
10.0000	7.0744	0.3235
15.0000	8.4410	0.2287
20.0000	9.4059	0.1594
25.0000	10.0493	0.1001
30.0000	10.4129	0.0450
35.0000	10.4911	-0.0135
40.0000	10.2906	-0.0657
45.0000	9.8438	-0.1114
50.0000	9.1921	-0.1479
55.0000	8.3775	-0.1766
60.0000	7.4333	-0.1995
65.0000	6.3890	-0.2162
70.0000	5.2835	-0.2240
75.0000	4.1572	-0.2241
80.0000	3.0531	-0.2151
85.0000	2.0217	-0.1959
90.0000	1.1116	-0.1658
95.0000	0.3924	-0.1179
100.0000	-0.0000	-0.0026
L.E. radius = 2.401 percent chord

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NACA Profile 63A006
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	0.5066	0.4617
0.7500	0.6082	0.3643
1.2500	0.7663	0.2796
2.5000	1.0534	0.1951
5.0000	1.4536	0.1354
7.5000	1.7530	0.1067
10.0000	1.9944	0.0882
15.0000	2.3664	0.0625
20.0000	2.6343	0.0448
25.0000	2.8224	0.0310
30.0000	2.9433	0.0178
35.0000	2.9956	0.0038
40.0000	2.9838	-0.0090
45.0000	2.9103	-0.0207
50.0000	2.7816	-0.0306
55.0000	2.6048	-0.0399
60.0000	2.3870	-0.0470
65.0000	2.1341	-0.0531
70.0000	1.8528	-0.0588
75.0000	1.5523	-0.0613
80.0000	1.2455	-0.0618
85.0000	0.9382	-0.0614
90.0000	0.6308	-0.0623
95.0000	0.3187	-0.0573
100.0000	0.0000	-2.3472
L.E. radius = 0.278 percent chord

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NACA Profile 63A008
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	0.6687	0.6119
0.7500	0.8037	0.4856
1.2500	1.0152	0.3748
2.5000	1.4004	0.2618
5.0000	1.9372	0.1816
7.5000	2.3384	0.1429
10.0000	2.6617	0.1181
15.0000	3.1595	0.0836
20.0000	3.5175	0.0598
25.0000	3.7684	0.0409
30.0000	3.9286	0.0231
35.0000	3.9957	0.0049
40.0000	3.9766	-0.0121
45.0000	3.8745	-0.0282
50.0000	3.6988	-0.0422
55.0000	3.4594	-0.0539
60.0000	3.1662	-0.0639
65.0000	2.8271	-0.0718
70.0000	2.4509	-0.0782
75.0000	2.0514	-0.0815
80.0000	1.6454	-0.0812
85.0000	1.2391	-0.0811
90.0000	0.8325	-0.0827
95.0000	0.4216	-0.0748
100.0000	0.0000	-3.8282
L.E. radius = 0.483 percent chord

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NACA Profile 63A010
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	0.8245	0.7591
0.7500	0.9925	0.6064
1.2500	1.2577	0.4713
2.5000	1.7425	0.3297
5.0000	2.4184	0.2284
7.5000	2.9228	0.1796
10.0000	3.3290	0.1482
15.0000	3.9537	0.1051
20.0000	4.4025	0.0750
25.0000	4.7162	0.0507
30.0000	4.9154	0.0279
35.0000	4.9963	0.0054
40.0000	4.9683	-0.0158
45.0000	4.8355	-0.0363
50.0000	4.6109	-0.0533
55.0000	4.3073	-0.0678
60.0000	3.9371	-0.0805
65.0000	3.5109	-0.0908
70.0000	3.0403	-0.0970
75.0000	2.5423	-0.1009
80.0000	2.0387	-0.1006
85.0000	1.5347	-0.1005
90.0000	1.0302	-0.1032
95.0000	0.5233	-0.0916
100.0000	0.0000	-6.0800
L.E. radius = 0.725 percent chord

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NACA Profile 63A012
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.9722	0.9023
0.7500	1.1725	0.7259
1.2500	1.4919	0.5693
2.5000	2.0782	0.3991
5.0000	2.8957	0.2760
7.5000	3.5051	0.2167
10.0000	3.9953	0.1786
15.0000	4.7484	0.1270
20.0000	5.2887	0.0903
25.0000	5.6657	0.0609
30.0000	5.9032	0.0322
35.0000	5.9971	0.0052
40.0000	5.9588	-0.0204
45.0000	5.7934	-0.0446
50.0000	5.5183	-0.0645
55.0000	5.1489	-0.0820
60.0000	4.7004	-0.0968
65.0000	4.1862	-0.1084
70.0000	3.6212	-0.1168
75.0000	3.0256	-0.1197
80.0000	2.4255	-0.1200
85.0000	1.8254	-0.1197
90.0000	1.2240	-0.1235
95.0000	0.6238	-0.1077
100.0000	0.0000	-9.5915
L.E. radius = 0.991 percent chord

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NACA Profile 63A015
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	1.1754	1.1071
0.7500	1.4221	0.9004
1.2500	1.8227	0.7195
2.5000	2.5656	0.5062
5.0000	3.6018	0.3494
7.5000	4.3723	0.2737
10.0000	4.9912	0.2249
15.0000	5.9404	0.1606
20.0000	6.6197	0.1138
25.0000	7.0924	0.0771
30.0000	7.3867	0.0391
35.0000	7.4983	0.0050
40.0000	7.4417	-0.0279
45.0000	7.2244	-0.0577
50.0000	6.8703	-0.0838
55.0000	6.3998	-0.1043
60.0000	5.8320	-0.1214
65.0000	5.1845	-0.1363
70.0000	4.4772	-0.1460
75.0000	3.7376	-0.1487
80.0000	2.9946	-0.1491
85.0000	2.2529	-0.1479
90.0000	1.5083	-0.1531
95.0000	0.7730	-0.1309
100.0000	0.0000	-19.2471
L.E. radius = 1.403 percent chord

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NACA Profile 64-006
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.4919	0.4693
0.7500	0.5954	0.3689
1.2500	0.7517	0.2693
2.5000	1.0216	0.1822
5.0000	1.4022	0.1300
7.5000	1.6897	0.1024
10.0000	1.9237	0.0860
15.0000	2.2931	0.0635
20.0000	2.5675	0.0471
25.0000	2.7676	0.0332
30.0000	2.9020	0.0207
35.0000	2.9761	0.0090
40.0000	2.9855	-0.0061
45.0000	2.9133	-0.0223
50.0000	2.7685	-0.0348
55.0000	2.5688	-0.0448
60.0000	2.3244	-0.0527
65.0000	2.0441	-0.0593
70.0000	1.7359	-0.0640
75.0000	1.4078	-0.0671
80.0000	1.0697	-0.0678
85.0000	0.7351	-0.0654
90.0000	0.4226	-0.0589
95.0000	0.1568	-0.0458
100.0000	0.0000	-0.0010
L.E. radius = 0.249 percent chord

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NACA Profile 64-008
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.6550	0.6243
0.7500	0.7928	0.4906
1.2500	1.0008	0.3590
2.5000	1.3615	0.2441
5.0000	1.8718	0.1743
7.5000	2.2570	0.1372
10.0000	2.5706	0.1152
15.0000	3.0654	0.0850
20.0000	3.4325	0.0630
25.0000	3.6995	0.0443
30.0000	3.8781	0.0271
35.0000	3.9754	0.0114
40.0000	3.9831	-0.0091
45.0000	3.8794	-0.0313
50.0000	3.6797	-0.0475
55.0000	3.4077	-0.0606
60.0000	3.0773	-0.0710
65.0000	2.7001	-0.0793
70.0000	2.2875	-0.0854
75.0000	1.8501	-0.0888
80.0000	1.4015	-0.0898
85.0000	0.9601	-0.0861
90.0000	0.5499	-0.0774
95.0000	0.2032	-0.0597
100.0000	-0.0000	-0.0013
L.E. radius = 0.447 percent chord

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NACA Profile 64-009
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	0.7360	0.7010
0.7500	0.8907	0.5510
1.2500	1.1245	0.4036
2.5000	1.5306	0.2752
5.0000	2.1064	0.1966
7.5000	2.5408	0.1547
10.0000	2.8946	0.1299
15.0000	3.4525	0.0958
20.0000	3.8661	0.0709
25.0000	4.1668	0.0498
30.0000	4.3673	0.0304
35.0000	4.4758	0.0125
40.0000	4.4817	-0.0110
45.0000	4.3608	-0.0361
50.0000	4.1326	-0.0542
55.0000	3.8234	-0.0687
60.0000	3.4492	-0.0804
65.0000	3.0232	-0.0893
70.0000	2.5581	-0.0961
75.0000	2.0661	-0.0999
80.0000	1.5628	-0.1006
85.0000	1.0689	-0.0962
90.0000	0.6112	-0.0861
95.0000	0.2255	-0.0663
100.0000	-0.0000	-0.0014
L.E. radius = 0.566 percent chord

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NACA Profile 64-010
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	0.8165	0.7773
0.7500	0.9880	0.6110
1.2500	1.2474	0.4482
2.5000	1.6991	0.3065
5.0000	2.3406	0.2191
7.5000	2.8246	0.1723
10.0000	3.2186	0.1446
15.0000	3.8400	0.1067
20.0000	4.3004	0.0789
25.0000	4.6346	0.0553
30.0000	4.8570	0.0337
35.0000	4.9766	0.0135
40.0000	4.9800	-0.0133
45.0000	4.8409	-0.0410
50.0000	4.5834	-0.0610
55.0000	4.2365	-0.0771
60.0000	3.8181	-0.0899
65.0000	3.3429	-0.0994
70.0000	2.8252	-0.1068
75.0000	2.2788	-0.1112
80.0000	1.7211	-0.1112
85.0000	1.1754	-0.1061
90.0000	0.6710	-0.0945
95.0000	0.2470	-0.0728
100.0000	0.0000	-0.0016
L.E. radius = 0.699 percent chord

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NACA Profile 64-012
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	0.9755	0.9276
0.7500	1.1802	0.7295
1.2500	1.4904	0.5368
2.5000	2.0331	0.3695
5.0000	2.8075	0.2645
7.5000	3.3914	0.2079
10.0000	3.8668	0.1743
15.0000	4.6159	0.1285
20.0000	5.1704	0.0950
25.0000	5.5721	0.0664
30.0000	5.8381	0.0407
35.0000	5.9789	0.0151
40.0000	5.9752	-0.0186
45.0000	5.7972	-0.0511
50.0000	5.4788	-0.0752
55.0000	5.0545	-0.0942
60.0000	4.5462	-0.1092
65.0000	3.9721	-0.1201
70.0000	3.3488	-0.1284
75.0000	2.6938	-0.1331
80.0000	2.0289	-0.1323
85.0000	1.3815	-0.1254
90.0000	0.7862	-0.1110
95.0000	0.2883	-0.0851
100.0000	-0.0000	-0.0019
L.E. radius = 1.005 percent chord

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NACA Profile 64-015
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	1.2077	1.1469
0.7500	1.4609	0.9029
1.2500	1.8458	0.6682
2.5000	2.5250	0.4649
5.0000	3.5019	0.3337
7.5000	4.2382	0.2621
10.0000	4.8374	0.2195
15.0000	5.7808	0.1616
20.0000	6.4780	0.1192
25.0000	6.9814	0.0831
30.0000	7.3125	0.0505
35.0000	7.4832	0.0171
40.0000	7.4629	-0.0275
45.0000	7.2202	-0.0682
50.0000	6.8050	-0.0971
55.0000	6.2609	-0.1195
60.0000	5.6145	-0.1376
65.0000	4.8898	-0.1513
70.0000	4.1079	-0.1608
75.0000	3.2917	-0.1647
80.0000	2.4688	-0.1633
85.0000	1.6740	-0.1536
90.0000	0.9484	-0.1353
95.0000	0.3459	-0.1023
100.0000	0.0000	-0.0023
L.E. radius = 1.557 percent chord

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NACA Profile 64-018
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	1.4300	1.3568
0.7500	1.7297	1.0699
1.2500	2.1872	0.7969
2.5000	3.0026	0.5615
5.0000	4.1862	0.4047
7.5000	5.0784	0.3174
10.0000	5.8041	0.2656
15.0000	6.9453	0.1952
20.0000	7.7873	0.1436
25.0000	8.3933	0.0998
30.0000	8.7891	0.0591
35.0000	8.9873	0.0182
40.0000	8.9432	-0.0372
45.0000	8.6277	-0.0862
50.0000	8.1107	-0.1195
55.0000	7.4421	-0.1463
60.0000	6.6541	-0.1674
65.0000	5.7770	-0.1831
70.0000	4.8364	-0.1924
75.0000	3.8609	-0.1964
80.0000	2.8841	-0.1926
85.0000	1.9477	-0.1802
90.0000	1.0988	-0.1572
95.0000	0.3988	-0.1186
100.0000	0.0000	-0.0027
L.E. radius = 2.208 percent chord

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NACA Profile 64-021
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	1.6399	1.5555
0.7500	1.9838	1.2290
1.2500	2.5114	0.9223
2.5000	3.4618	0.6591
5.0000	4.8572	0.4776
7.5000	5.9094	0.3742
10.0000	6.7645	0.3128
15.0000	8.1078	0.2295
20.0000	9.0971	0.1683
25.0000	9.8069	0.1163
30.0000	10.2669	0.0680
35.0000	10.4903	0.0180
40.0000	10.4155	-0.0487
45.0000	10.0198	-0.1044
50.0000	9.3950	-0.1436
55.0000	8.5971	-0.1745
60.0000	7.6648	-0.1972
65.0000	6.6334	-0.2140
70.0000	5.5351	-0.2243
75.0000	4.4025	-0.2274
80.0000	3.2762	-0.2217
85.0000	2.2043	-0.2054
90.0000	1.2386	-0.1783
95.0000	0.4474	-0.1335
100.0000	-0.0000	-0.0031
L.E. radius = 2.941 percent chord

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NACA Profile 64A006
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.5015	0.4570
0.7500	0.6018	0.3569
1.2500	0.7543	0.2661
2.5000	1.0267	0.1843
5.0000	1.4041	0.1274
7.5000	1.6870	0.1018
10.0000	1.9208	0.0858
15.0000	2.2864	0.0627
20.0000	2.5592	0.0469
25.0000	2.7592	0.0333
30.0000	2.8967	0.0214
35.0000	2.9767	0.0103
40.0000	2.9978	-0.0027
45.0000	2.9439	-0.0179
50.0000	2.8245	-0.0295
55.0000	2.6522	-0.0391
60.0000	2.4371	-0.0470
65.0000	2.1857	-0.0537
70.0000	1.9034	-0.0592
75.0000	1.5997	-0.0621
80.0000	1.2850	-0.0633
85.0000	0.9678	-0.0629
90.0000	0.6512	-0.0650
95.0000	0.3290	-0.0595
100.0000	0.0000	-2.3490
L.E. radius = 0.277 percent chord

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NACA Profile 64A008
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	0.6614	0.6055
0.7500	0.7945	0.4749
1.2500	0.9981	0.3560
2.5000	1.3631	0.2471
5.0000	1.8692	0.1706
7.5000	2.2484	0.1364
10.0000	2.5615	0.1148
15.0000	3.0508	0.0839
20.0000	3.4157	0.0628
25.0000	3.6826	0.0443
30.0000	3.8657	0.0288
35.0000	3.9715	0.0139
40.0000	3.9965	-0.0046
45.0000	3.9194	-0.0249
50.0000	3.7558	-0.0399
55.0000	3.5222	-0.0528
60.0000	3.2325	-0.0630
65.0000	2.8951	-0.0719
70.0000	2.5177	-0.0787
75.0000	2.1138	-0.0825
80.0000	1.6967	-0.0840
85.0000	1.2777	-0.0831
90.0000	0.8587	-0.0858
95.0000	0.4349	-0.0777
100.0000	0.0000	-3.8252
L.E. radius = 0.485 percent chord

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NACA Profile 64A010
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	0.8148	0.7509
0.7500	0.9802	0.5920
1.2500	1.2351	0.4467
2.5000	1.6938	0.3110
5.0000	2.3307	0.2145
7.5000	2.8075	0.1713
10.0000	3.2010	0.1441
15.0000	3.8152	0.1053
20.0000	4.2731	0.0789
25.0000	4.6073	0.0555
30.0000	4.8361	0.0361
35.0000	4.9672	0.0172
40.0000	4.9946	-0.0073
45.0000	4.8920	-0.0321
50.0000	4.6822	-0.0509
55.0000	4.3855	-0.0664
60.0000	4.0198	-0.0792
65.0000	3.5954	-0.0903
70.0000	3.1228	-0.0982
75.0000	2.6192	-0.1027
80.0000	2.1010	-0.1042
85.0000	1.5817	-0.1040
90.0000	1.0620	-0.1061
95.0000	0.5393	-0.0950
100.0000	0.0000	-6.0619
L.E. radius = 0.736 percent chord

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NACA Profile 64A012
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.9599	0.8923
0.7500	1.1571	0.7078
1.2500	1.4632	0.5383
2.5000	2.0172	0.3761
5.0000	2.7874	0.2592
7.5000	3.3633	0.2068
10.0000	3.8383	0.1738
15.0000	4.5791	0.1269
20.0000	5.1309	0.0950
25.0000	5.5329	0.0667
30.0000	5.8077	0.0435
35.0000	5.9638	0.0201
40.0000	5.9916	-0.0106
45.0000	5.8615	-0.0399
50.0000	5.6034	-0.0627
55.0000	5.2423	-0.0808
60.0000	4.7994	-0.0956
65.0000	4.2870	-0.1089
70.0000	3.7191	-0.1176
75.0000	3.1163	-0.1230
80.0000	2.4983	-0.1240
85.0000	1.8801	-0.1237
90.0000	1.2613	-0.1263
95.0000	0.6424	-0.1117
100.0000	0.0000	-9.5354
L.E. radius = 1.021 percent chord

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NACA Profile 64A015
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	1.1586	1.0948
0.7500	1.4015	0.8775
1.2500	1.7844	0.6772
2.5000	2.4845	0.4765
5.0000	3.4601	0.3280
7.5000	4.1883	0.2613
10.0000	4.7882	0.2192
15.0000	5.7223	0.1600
20.0000	6.4174	0.1193
25.0000	6.9224	0.0841
30.0000	7.2668	0.0542
35.0000	7.4597	0.0235
40.0000	7.4852	-0.0161
45.0000	7.3100	-0.0526
50.0000	6.9761	-0.0806
55.0000	6.5154	-0.1029
60.0000	5.9546	-0.1214
65.0000	5.3091	-0.1356
70.0000	4.5981	-0.1470
75.0000	3.8475	-0.1525
80.0000	3.0824	-0.1531
85.0000	2.3189	-0.1510
90.0000	1.5532	-0.1567
95.0000	0.7951	-0.1356
100.0000	0.0000	-19.0255
L.E. radius = 1.481 percent chord

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NACA Profile 65-006
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	0.4680	0.4374
0.7500	0.5639	0.3386
1.2500	0.7052	0.2420
2.5000	0.9520	0.1691
5.0000	1.3110	0.1245
7.5000	1.5905	0.1012
10.0000	1.8243	0.0862
15.0000	2.1977	0.0646
20.0000	2.4814	0.0494
25.0000	2.6957	0.0368
30.0000	2.8510	0.0255
35.0000	2.9505	0.0144
40.0000	2.9971	0.0035
45.0000	2.9819	-0.0099
50.0000	2.8978	-0.0238
55.0000	2.7413	-0.0383
60.0000	2.5198	-0.0498
65.0000	2.2475	-0.0585
70.0000	1.9345	-0.0665
75.0000	1.5921	-0.0704
80.0000	1.2311	-0.0734
85.0000	0.8633	-0.0729
90.0000	0.5069	-0.0686
95.0000	0.1892	-0.0558
100.0000	-0.0000	-0.0008
L.E. radius = 0.230 percent chord

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NACA Profile 65-008
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	0.6205	0.5804
0.7500	0.7477	0.4492
1.2500	0.9355	0.3224
2.5000	1.2653	0.2265
5.0000	1.7464	0.1668
7.5000	2.1204	0.1355
10.0000	2.4333	0.1153
15.0000	2.9327	0.0864
20.0000	3.3120	0.0660
25.0000	3.5981	0.0492
30.0000	3.8050	0.0337
35.0000	3.9370	0.0192
40.0000	3.9975	0.0042
45.0000	3.9733	-0.0140
50.0000	3.8556	-0.0332
55.0000	3.6401	-0.0524
60.0000	3.3388	-0.0671
65.0000	2.9714	-0.0792
70.0000	2.5508	-0.0882
75.0000	2.0943	-0.0937
80.0000	1.6145	-0.0974
85.0000	1.1286	-0.0962
90.0000	0.6602	-0.0902
95.0000	0.2463	-0.0723
100.0000	0.0000	-0.0011
L.E. radius = 0.406 percent chord

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NACA Profile 65-009
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	0.6955	0.6511
0.7500	0.8383	0.5039
1.2500	1.0492	0.3626
2.5000	1.4206	0.2554
5.0000	1.9632	0.1881
7.5000	2.3850	0.1528
10.0000	2.7377	0.1299
15.0000	3.3004	0.0973
20.0000	3.7276	0.0743
25.0000	4.0499	0.0554
30.0000	4.2826	0.0378
35.0000	4.4307	0.0217
40.0000	4.4978	0.0045
45.0000	4.4684	-0.0162
50.0000	4.3329	-0.0382
55.0000	4.0865	-0.0596
60.0000	3.7443	-0.0761
65.0000	3.3284	-0.0897
70.0000	2.8539	-0.0989
75.0000	2.3402	-0.1053
80.0000	1.8014	-0.1094
85.0000	1.2573	-0.1078
90.0000	0.7342	-0.1005
95.0000	0.2739	-0.0802
100.0000	0.0000	-0.0012
L.E. radius = 0.510 percent chord

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NACA Profile 65-010
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	0.7697	0.7211
0.7500	0.9278	0.5582
1.2500	1.1616	0.4026
2.5000	1.5748	0.2844
5.0000	2.1794	0.2096
7.5000	2.6491	0.1701
10.0000	3.0418	0.1446
15.0000	3.6681	0.1083
20.0000	4.1435	0.0827
25.0000	4.5020	0.0616
30.0000	4.7605	0.0418
35.0000	4.9247	0.0240
40.0000	4.9981	0.0047
45.0000	4.9631	-0.0184
50.0000	4.8089	-0.0434
55.0000	4.5309	-0.0670
60.0000	4.1471	-0.0853
65.0000	3.6823	-0.1000
70.0000	3.1537	-0.1103
75.0000	2.5827	-0.1172
80.0000	1.9851	-0.1213
85.0000	1.3834	-0.1191
90.0000	0.8064	-0.1105
95.0000	0.3010	-0.0878
100.0000	0.0000	-0.0014
L.E. radius = 0.624 percent chord

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NACA Profile 65-012
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.9146	0.8590
0.7500	1.1031	0.6655
1.2500	1.3824	0.4823
2.5000	1.8792	0.3430
5.0000	2.6091	0.2529
7.5000	3.1756	0.2052
10.0000	3.6490	0.1742
15.0000	4.4035	0.1304
20.0000	4.9758	0.0995
25.0000	5.4070	0.0741
30.0000	5.7172	0.0500
35.0000	5.9135	0.0287
40.0000	5.9990	0.0047
45.0000	5.9512	-0.0235
50.0000	5.7573	-0.0545
55.0000	5.4137	-0.0821
60.0000	4.9445	-0.1044
65.0000	4.3806	-0.1207
70.0000	3.7427	-0.1342
75.0000	3.0576	-0.1408
80.0000	2.3433	-0.1440
85.0000	1.6282	-0.1411
90.0000	0.9461	-0.1298
95.0000	0.3534	-0.1025
100.0000	0.0000	-0.0016
L.E. radius = 0.876 percent chord

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NACA Profile 65-015
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	1.1222	1.0592
0.7500	1.3548	0.8223
1.2500	1.7012	0.6006
2.5000	2.3240	0.4323
5.0000	3.2454	0.3192
7.5000	3.9598	0.2586
10.0000	4.5562	0.2194
15.0000	5.5056	0.1640
20.0000	6.2249	0.1250
25.0000	6.7662	0.0928
30.0000	7.1543	0.0626
35.0000	7.3985	0.0352
40.0000	7.5004	0.0041
45.0000	7.4295	-0.0333
50.0000	7.1704	-0.0710
55.0000	6.7225	-0.1065
60.0000	6.1200	-0.1335
65.0000	5.4045	-0.1532
70.0000	4.6011	-0.1664
75.0000	3.7453	-0.1752
80.0000	2.8588	-0.1780
85.0000	1.9777	-0.1733
90.0000	1.1444	-0.1576
95.0000	0.4281	-0.1237
100.0000	0.0000	-0.0020
L.E. radius = 1.301 percent chord

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NACA Profile 65-018
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	1.3152	1.2496
0.7500	1.5900	0.9735
1.2500	2.0018	0.7165
2.5000	2.7507	0.5233
5.0000	3.8687	0.3873
7.5000	4.7349	0.3133
10.0000	5.4570	0.2655
15.0000	6.6050	0.1983
20.0000	7.4738	0.1508
25.0000	8.1267	0.1117
30.0000	8.5934	0.0756
35.0000	8.8854	0.0416
40.0000	9.0016	0.0028
45.0000	8.9025	-0.0429
50.0000	8.5722	-0.0897
55.0000	8.0118	-0.1323
60.0000	7.2713	-0.1622
65.0000	6.4011	-0.1846
70.0000	5.4316	-0.1999
75.0000	4.4047	-0.2097
80.0000	3.3493	-0.2107
85.0000	2.3072	-0.2042
90.0000	1.3305	-0.1838
95.0000	0.4987	-0.1440
100.0000	0.0000	-0.0024
L.E. radius = 1.756 percent chord

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NACA Profile 65-021
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	1.4909	1.4278
0.7500	1.8058	1.1178
1.2500	2.2805	0.8291
2.5000	3.1550	0.6160
5.0000	4.4755	0.4575
7.5000	5.4980	0.3695
10.0000	6.3493	0.3127
15.0000	7.7005	0.2333
20.0000	8.7216	0.1771
25.0000	9.4880	0.1307
30.0000	10.0344	0.0884
35.0000	10.3740	0.0480
40.0000	10.5025	0.0008
45.0000	10.3711	-0.0524
50.0000	9.9609	-0.1119
55.0000	9.2823	-0.1578
60.0000	8.3992	-0.1915
65.0000	7.3699	-0.2198
70.0000	6.2331	-0.2360
75.0000	5.0374	-0.2428
80.0000	3.8165	-0.2435
85.0000	2.6181	-0.2338
90.0000	1.5056	-0.2083
95.0000	0.5656	-0.1630
100.0000	0.0000	-0.0027
L.E. radius = 2.212 percent chord

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NACA Profile 65A006
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.4785	0.4384
0.7500	0.5757	0.3509
1.2500	0.7279	0.2661
2.5000	0.9890	0.1677
5.0000	1.3199	0.1156
7.5000	1.5958	0.1025
10.0000	1.8282	0.0852
15.0000	2.1962	0.0637
20.0000	2.4754	0.0484
25.0000	2.6872	0.0362
30.0000	2.8415	0.0259
35.0000	2.9439	0.0157
40.0000	2.9949	0.0049
45.0000	2.9908	-0.0064
50.0000	2.9247	-0.0196
55.0000	2.7931	-0.0326
60.0000	2.6014	-0.0437
65.0000	2.3631	-0.0519
70.0000	2.0859	-0.0591
75.0000	1.7752	-0.0651
80.0000	1.4389	-0.0692
85.0000	1.0858	-0.0713
90.0000	0.7307	-0.0720
95.0000	0.3693	-0.0677
100.0000	0.0000	-2.3467
L.E. radius = 0.253 percent chord

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NACA Profile 65A008
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	0.6303	0.5823
0.7500	0.7597	0.4686
1.2500	0.9633	0.3560
2.5000	1.3124	0.2240
5.0000	1.7556	0.1552
7.5000	2.1256	0.1371
10.0000	2.4365	0.1140
15.0000	2.9289	0.0852
20.0000	3.3022	0.0648
25.0000	3.5851	0.0484
30.0000	3.7910	0.0344
35.0000	3.9273	0.0208
40.0000	3.9942	0.0063
45.0000	3.9866	-0.0093
50.0000	3.8946	-0.0271
55.0000	3.7143	-0.0447
60.0000	3.4545	-0.0587
65.0000	3.1338	-0.0697
70.0000	2.7623	-0.0792
75.0000	2.3473	-0.0868
80.0000	1.8997	-0.0927
85.0000	1.4320	-0.0937
90.0000	0.9626	-0.0957
95.0000	0.4873	-0.0886
100.0000	0.0000	-3.8098
L.E. radius = 0.437 percent chord

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NACA Profile 65A010
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	0.7753	0.7243
0.7500	0.9368	0.5866
1.2500	1.1923	0.4471
2.5000	1.6303	0.2809
5.0000	2.1872	0.1953
7.5000	2.6525	0.1722
10.0000	3.0429	0.1432
15.0000	3.6607	0.1069
20.0000	4.1288	0.0812
25.0000	4.4834	0.0608
30.0000	4.7413	0.0428
35.0000	4.9114	0.0256
40.0000	4.9938	0.0075
45.0000	4.9816	-0.0126
50.0000	4.8618	-0.0353
55.0000	4.6306	-0.0572
60.0000	4.3010	-0.0739
65.0000	3.8966	-0.0876
70.0000	3.4298	-0.0994
75.0000	2.9104	-0.1081
80.0000	2.3518	-0.1149
85.0000	1.7714	-0.1158
90.0000	1.1893	-0.1188
95.0000	0.6033	-0.1089
100.0000	0.0000	-6.0159
L.E. radius = 0.654 percent chord

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NACA Profile 65A012
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.9120	0.8634
0.7500	1.1052	0.7047
1.2500	1.4133	0.5398
2.5000	1.9415	0.3385
5.0000	2.6134	0.2360
7.5000	3.1755	0.2077
10.0000	3.6465	0.1726
15.0000	4.3911	0.1288
20.0000	4.9550	0.0979
25.0000	5.3819	0.0733
30.0000	5.6920	0.0511
35.0000	5.8961	0.0304
40.0000	5.9937	0.0087
45.0000	5.9758	-0.0163
50.0000	5.8264	-0.0435
55.0000	5.5421	-0.0698
60.0000	5.1411	-0.0896
65.0000	4.6518	-0.1054
70.0000	4.0889	-0.1190
75.0000	3.4650	-0.1291
80.0000	2.7959	-0.1367
85.0000	2.1043	-0.1379
90.0000	1.4110	-0.1410
95.0000	0.7173	-0.1284
100.0000	0.0000	-9.4312
L.E. radius = 0.890 percent chord

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NACA Profile 65A015
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	1.0979	1.0636
0.7500	1.3375	0.8799
1.2500	1.7256	0.6825
2.5000	2.3921	0.4268
5.0000	3.2399	0.2980
7.5000	3.9501	0.2624
10.0000	4.5444	0.2177
15.0000	5.4826	0.1622
20.0000	6.1922	0.1232
25.0000	6.7291	0.0925
30.0000	7.1185	0.0639
35.0000	7.3738	0.0375
40.0000	7.4938	0.0099
45.0000	7.4655	-0.0224
50.0000	7.2686	-0.0560
55.0000	6.9009	-0.0889
60.0000	6.3898	-0.1141
65.0000	5.7711	-0.1327
70.0000	5.0631	-0.1489
75.0000	4.2819	-0.1620
80.0000	3.4477	-0.1710
85.0000	2.5920	-0.1710
90.0000	1.7352	-0.1742
95.0000	0.8854	-0.1559
100.0000	0.0000	-18.7976
L.E. radius = 1.253 percent chord

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NACA Profile 66-006
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.4592	0.4300
0.7500	0.5529	0.3294
1.2500	0.6896	0.2309
2.5000	0.9174	0.1553
5.0000	1.2562	0.1199
7.5000	1.5255	0.0975
10.0000	1.7511	0.0840
15.0000	2.1187	0.0641
20.0000	2.3999	0.0493
25.0000	2.6171	0.0378
30.0000	2.7810	0.0279
35.0000	2.8973	0.0190
40.0000	2.9697	0.0100
45.0000	2.9986	0.0013
50.0000	2.9839	-0.0074
55.0000	2.9229	-0.0172
60.0000	2.8083	-0.0296
65.0000	2.6116	-0.0504
70.0000	2.3136	-0.0676
75.0000	1.9511	-0.0773
80.0000	1.5436	-0.0853
85.0000	1.1066	-0.0884
90.0000	0.6681	-0.0862
95.0000	0.2625	-0.0732
100.0000	0.0000	-0.0009
L.E. radius = 0.218 percent chord

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NACA Profile 66-008
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	0.6099	0.5690
0.7500	0.7338	0.4356
1.2500	0.9147	0.3062
2.5000	1.2182	0.2079
5.0000	1.6719	0.1605
7.5000	2.0320	0.1303
10.0000	2.3337	0.1123
15.0000	2.8248	0.0857
20.0000	3.2003	0.0658
25.0000	3.4903	0.0505
30.0000	3.7091	0.0373
35.0000	3.8642	0.0253
40.0000	3.9604	0.0131
45.0000	3.9984	0.0016
50.0000	3.9777	-0.0102
55.0000	3.8946	-0.0236
60.0000	3.7378	-0.0408
65.0000	3.4657	-0.0694
70.0000	3.0592	-0.0915
75.0000	2.5714	-0.1039
80.0000	2.0258	-0.1137
85.0000	1.4453	-0.1169
90.0000	0.8674	-0.1131
95.0000	0.3381	-0.0952
100.0000	0.0000	-0.0011
L.E. radius = 0.390 percent chord

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NACA Profile 66-009
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.6844	0.6373
0.7500	0.8231	0.4878
1.2500	1.0259	0.3435
2.5000	1.3672	0.2343
5.0000	1.8787	0.1809
7.5000	2.2845	0.1468
10.0000	2.6244	0.1266
15.0000	3.1776	0.0965
20.0000	3.6004	0.0741
25.0000	3.9270	0.0569
30.0000	4.1733	0.0419
35.0000	4.3478	0.0284
40.0000	4.4558	0.0147
45.0000	4.4983	0.0018
50.0000	4.4745	-0.0117
55.0000	4.3799	-0.0268
60.0000	4.2012	-0.0468
65.0000	3.8895	-0.0789
70.0000	3.4272	-0.1034
75.0000	2.8760	-0.1172
80.0000	2.2610	-0.1280
85.0000	1.6093	-0.1310
90.0000	0.9631	-0.1260
95.0000	0.3739	-0.1057
100.0000	-0.0000	-0.0013
L.E. radius = 0.493 percent chord

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NACA Profile 66-010
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	0.7582	0.7047
0.7500	0.9116	0.5393
1.2500	1.1360	0.3804
2.5000	1.5150	0.2609
5.0000	2.0846	0.2014
7.5000	2.5364	0.1634
10.0000	2.9146	0.1408
15.0000	3.5301	0.1073
20.0000	4.0003	0.0824
25.0000	4.3635	0.0634
30.0000	4.6374	0.0466
35.0000	4.8314	0.0315
40.0000	4.9513	0.0163
45.0000	4.9983	0.0019
50.0000	4.9712	-0.0132
55.0000	4.8649	-0.0300
60.0000	4.6636	-0.0530
65.0000	4.3111	-0.0887
70.0000	3.7920	-0.1154
75.0000	3.1768	-0.1305
80.0000	2.4922	-0.1423
85.0000	1.7699	-0.1449
90.0000	1.0561	-0.1388
95.0000	0.4084	-0.1158
100.0000	0.0000	-0.0014
L.E. radius = 0.608 percent chord

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NACA Profile 66-012
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.9039	0.8364
0.7500	1.0858	0.6399
1.2500	1.3525	0.4534
2.5000	1.8067	0.3142
5.0000	2.4936	0.2428
7.5000	3.0378	0.1968
10.0000	3.4933	0.1696
15.0000	4.2340	0.1292
20.0000	4.7996	0.0991
25.0000	5.2364	0.0763
30.0000	5.5656	0.0560
35.0000	5.7987	0.0376
40.0000	5.9424	0.0197
45.0000	5.9981	0.0022
50.0000	5.9642	-0.0163
55.0000	5.8339	-0.0366
60.0000	5.5857	-0.0659
65.0000	5.1477	-0.1097
70.0000	4.5122	-0.1398
75.0000	3.7677	-0.1571
80.0000	2.9432	-0.1706
85.0000	2.0807	-0.1723
90.0000	1.2346	-0.1643
95.0000	0.4738	-0.1352
100.0000	0.0000	-0.0016
L.E. radius = 0.871 percent chord

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NACA Profile 66-015
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	1.1157	1.0250
0.7500	1.3386	0.7842
1.2500	1.6666	0.5600
2.5000	2.2326	0.3948
5.0000	3.0980	0.3059
7.5000	3.7831	0.2476
10.0000	4.3558	0.2132
15.0000	5.2863	0.1622
20.0000	5.9963	0.1245
25.0000	6.5444	0.0959
30.0000	6.9573	0.0701
35.0000	7.2494	0.0467
40.0000	7.4291	0.0251
45.0000	7.4979	0.0027
50.0000	7.4531	-0.0208
55.0000	7.2853	-0.0468
60.0000	6.9614	-0.0866
65.0000	6.3846	-0.1441
70.0000	5.5686	-0.1781
75.0000	4.6263	-0.1992
80.0000	3.5911	-0.2135
85.0000	2.5222	-0.2125
90.0000	1.4839	-0.2004
95.0000	0.5635	-0.1619
100.0000	0.0000	-0.0020
L.E. radius = 1.345 percent chord

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NACA Profile 66-018
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	1.3179	1.2013
0.7500	1.5791	0.9195
1.2500	1.9652	0.6626
2.5000	2.6413	0.4758
5.0000	3.6886	0.3704
7.5000	4.5176	0.2993
10.0000	5.2097	0.2575
15.0000	6.3330	0.1957
20.0000	7.1892	0.1502
25.0000	7.8502	0.1157
30.0000	8.3477	0.0844
35.0000	8.6995	0.0561
40.0000	8.9159	0.0305
45.0000	8.9977	0.0031
50.0000	8.9415	-0.0250
55.0000	8.7343	-0.0579
60.0000	8.3274	-0.1101
65.0000	7.5989	-0.1800
70.0000	6.5958	-0.2169
75.0000	5.4522	-0.2400
80.0000	4.2058	-0.2540
85.0000	2.9351	-0.2516
90.0000	1.7130	-0.2334
95.0000	0.6441	-0.1860
100.0000	-0.0000	-0.0023
L.E. radius = 1.904 percent chord

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NACA Profile 66-021
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	1.5086	1.3639
0.7500	1.8051	1.0446
1.2500	2.2457	0.7602
2.5000	3.0294	0.5566
5.0000	4.2624	0.4366
7.5000	5.2389	0.3522
10.0000	6.0529	0.3027
15.0000	7.3726	0.2298
20.0000	8.3773	0.1763
25.0000	9.1527	0.1359
30.0000	9.7361	0.0990
35.0000	10.1487	0.0661
40.0000	10.4025	0.0355
45.0000	10.4976	0.0034
50.0000	10.4297	-0.0298
55.0000	10.1809	-0.0700
60.0000	9.6829	-0.1354
65.0000	8.7908	-0.2154
70.0000	7.5948	-0.2551
75.0000	6.2451	-0.2837
80.0000	4.7886	-0.2961
85.0000	3.3209	-0.2893
90.0000	1.9235	-0.2653
95.0000	0.7166	-0.2083
100.0000	0.0000	-0.0026
L.E. radius = 2.537 percent chord

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NACA Profile 67-012
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	********
0.5000	0.9505	0.8499
0.7500	1.1372	0.6774
1.2500	1.4355	0.5217
2.5000	1.9412	0.3300
5.0000	2.6174	0.2313
7.5000	3.1377	0.1867
10.0000	3.5617	0.1550
15.0000	4.2379	0.1179
20.0000	4.7606	0.0919
25.0000	5.1698	0.0717
30.0000	5.4878	0.0550
35.0000	5.7271	0.0399
40.0000	5.8891	0.0251
45.0000	5.9804	0.0111
50.0000	5.9972	-0.0042
55.0000	5.9368	-0.0206
60.0000	5.7860	-0.0404
65.0000	5.5292	-0.0634
70.0000	5.1376	-0.0965
75.0000	4.5357	-0.1462
80.0000	3.6903	-0.1849
85.0000	2.7246	-0.2018
90.0000	1.6745	-0.2137
95.0000	0.6565	-0.1842
100.0000	0.0000	-0.0030
L.E. radius = 1.012 percent chord

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NACA Profile 67-015
(Stations and ordinates given in per cent of airfoil chord)
x	y	dy/dx
0.0000	0.0000	0.0000
0.5000	1.1649	1.0304
0.7500	1.3922	0.8322
1.2500	1.7626	0.6506
2.5000	2.3941	0.4134
5.0000	3.2443	0.2913
7.5000	3.8995	0.2350
10.0000	4.4329	0.1949
15.0000	5.2829	0.1482
20.0000	5.9398	0.1155
25.0000	6.4539	0.0902
30.0000	6.8539	0.0696
35.0000	7.1550	0.0501
40.0000	7.3593	0.0317
45.0000	7.4750	0.0143
50.0000	7.4969	-0.0046
55.0000	7.4214	-0.0261
60.0000	7.2309	-0.0513
65.0000	6.9052	-0.0805
70.0000	6.4023	-0.1249
75.0000	5.6213	-0.1886
80.0000	4.5401	-0.2336
85.0000	3.3271	-0.2539
90.0000	2.0210	-0.2618
95.0000	0.7880	-0.2209
100.0000	0.0000	-0.0037
L.E. radius = 1.570 percent chord

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Public Domain Aeronautical Software (PDAS)

Appendix I - Profiles