COORDINATES OF NACA AIRFOILS Created by naca456, version 1.0 (4 January 2002) on 14:10 8Dec2009 Ralph L. Carmichael, Public Domain Aeronautical Software NACA 64A004.29 Six-series profile, family= 64A t/c= 0.0429 Six-series mean line (modified), cl= 0.0000 (a=0.8 always for 6M) SYMMETRICAL AIRFOIL DEFINITION x y dy/dx 1 0.000000 0.000000********** 2 0.000200 0.000759 1.888130 3 0.000500 0.001196 1.181255 4 0.001000 0.001681 0.821542 5 0.001500 0.002047 0.660115 6 0.002000 0.002351 0.562445 7 0.005000 0.003609 0.328207 8 0.010000 0.004914 0.215670 9 0.015000 0.005869 0.172029 10 0.020000 0.006664 0.147745 11 0.030000 0.007982 0.119038 12 0.040000 0.009083 0.102266 13 0.050000 0.010045 0.090765 14 0.060000 0.010906 0.082183 15 0.080000 0.012416 0.069923 16 0.100000 0.013726 0.061185 17 0.120000 0.014868 0.053374 18 0.140000 0.015873 0.047323 19 0.160000 0.016768 0.042268 20 0.180000 0.017568 0.037701 21 0.200000 0.018280 0.033399 22 0.220000 0.018908 0.029531 23 0.240000 0.019459 0.025721 24 0.260000 0.019938 0.022173 25 0.280000 0.020348 0.018802 26 0.300000 0.020694 0.015308 27 0.320000 0.020974 0.012419 28 0.340000 0.021189 0.009172 29 0.360000 0.021340 0.006240 30 0.380000 0.021425 0.002735 31 0.400000 0.021435 -0.001540 32 0.420000 0.021356 -0.006286 33 0.440000 0.021189 -0.010597 34 0.460000 0.020941 -0.014155 35 0.480000 0.020624 -0.017406 36 0.500000 0.020241 -0.020636 37 0.520000 0.019799 -0.023684 38 0.540000 0.019299 -0.026564 39 0.560000 0.018745 -0.028802 40 0.580000 0.018147 -0.030971 41 0.600000 0.017504 -0.033279 42 0.620000 0.016819 -0.035224 43 0.640000 0.016093 -0.037176 44 0.660000 0.015331 -0.039105 45 0.680000 0.014534 -0.040706 46 0.700000 0.013704 -0.042456 47 0.720000 0.012848 -0.043225 48 0.740000 0.011971 -0.044134 49 0.760000 0.011081 -0.044901 50 0.780000 0.010177 -0.045261 51 0.800000 0.009266 -0.045511 52 0.820000 0.008352 -0.045698 53 0.840000 0.007437 -0.045857 54 0.860000 0.006527 -0.045826 55 0.880000 0.005618 -0.045475 56 0.900000 0.004702 -0.046583 57 0.920000 0.003758 -0.047533 58 0.940000 0.002817 -0.045688 59 0.960000 0.001955 -0.039934 60 0.970000 0.001570 -0.037455 61 0.980000 0.001201 -0.036847 62 0.990000 0.000808 -0.043386 63 0.995000 0.000563 -0.057588 64 1.000000 -0.000000 -1.471364 End of output for symmetrical airfoil