COORDINATES OF NACA AIRFOILS Created by naca456, version 1.0 (4 January 2002) on 14:07 8Dec2009 Ralph L. Carmichael, Public Domain Aeronautical Software NACA 64A005.92 Six-series profile, family= 64A t/c= 0.0592 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 0.001039 2.584791 3 0.000500 0.001638 1.619233 4 0.001000 0.002303 1.126466 5 0.001500 0.002805 0.905521 6 0.002000 0.003222 0.771981 7 0.005000 0.004950 0.451065 8 0.010000 0.006747 0.297989 9 0.015000 0.008069 0.238172 10 0.020000 0.009168 0.204673 11 0.030000 0.010995 0.164998 12 0.040000 0.012521 0.141642 13 0.050000 0.013854 0.125644 14 0.060000 0.015046 0.113739 15 0.080000 0.017138 0.096923 16 0.100000 0.018951 0.084637 17 0.120000 0.020531 0.073810 18 0.140000 0.021922 0.065470 19 0.160000 0.023159 0.058477 20 0.180000 0.024266 0.052109 21 0.200000 0.025250 0.046216 22 0.220000 0.026118 0.040750 23 0.240000 0.026879 0.035636 24 0.260000 0.027539 0.030722 25 0.280000 0.028104 0.025990 26 0.300000 0.028579 0.021119 27 0.320000 0.028965 0.016926 28 0.340000 0.029258 0.012392 29 0.360000 0.029464 0.008183 30 0.380000 0.029575 0.003343 31 0.400000 0.029578 -0.002607 32 0.420000 0.029457 -0.009041 33 0.440000 0.029212 -0.015192 34 0.460000 0.028859 -0.020105 35 0.480000 0.028410 -0.024924 36 0.500000 0.027871 -0.029068 37 0.520000 0.027250 -0.033110 38 0.540000 0.026549 -0.037024 39 0.560000 0.025779 -0.039992 40 0.580000 0.024946 -0.043258 41 0.600000 0.024051 -0.046321 42 0.620000 0.023100 -0.049076 43 0.640000 0.022093 -0.051461 44 0.660000 0.021036 -0.054142 45 0.680000 0.019932 -0.056860 46 0.700000 0.018786 -0.058418 47 0.720000 0.017607 -0.059707 48 0.740000 0.016399 -0.060675 49 0.760000 0.015174 -0.061792 50 0.780000 0.013933 -0.062129 51 0.800000 0.012683 -0.062413 52 0.820000 0.011430 -0.062933 53 0.840000 0.010177 -0.062449 54 0.860000 0.008929 -0.062502 55 0.880000 0.007686 -0.062395 56 0.900000 0.006429 -0.064136 57 0.920000 0.005135 -0.065052 58 0.940000 0.003853 -0.062109 59 0.960000 0.002683 -0.054266 60 0.970000 0.002160 -0.051036 61 0.980000 0.001655 -0.050465 62 0.990000 0.001116 -0.059728 63 0.995000 0.000778 -0.079570 64 1.000000 -0.000000 -2.315517 End of output for symmetrical airfoil