COORDINATES OF NACA AIRFOILS Created by naca456, version 1.0 (4 January 2002) on 17:46 4Jan2002 Ralph L. Carmichael, Public Domain Aeronautical Software NACA 63A409 Six-series profile, family= 63A t/c= 0.0900 Six-series mean line (modified), cl= 0.4000 (a=0.8 always for 6M) THICKNESS MEAN LINE x y dy/dx y dy/dx 1 0.000000 0.000000********** 0.000000 0.000000 2 0.005000 0.007475 0.685945 0.001124 0.190157 3 0.007500 0.008990 0.546120 0.001581 0.176014 4 0.012500 0.011374 0.422836 0.002413 0.158122 5 0.025000 0.015721 0.295641 0.004219 0.133617 6 0.050000 0.021782 0.204877 0.007212 0.108596 7 0.075000 0.026308 0.161164 0.009727 0.093511 8 0.100000 0.029954 0.133090 0.011921 0.082474 9 0.150000 0.035565 0.094277 0.015614 0.066179 10 0.200000 0.039598 0.067383 0.018602 0.053808 11 0.250000 0.042421 0.045810 0.021028 0.043491 12 0.300000 0.044218 0.025529 0.022971 0.034378 13 0.350000 0.044960 0.005262 0.024478 0.025993 14 0.400000 0.044726 -0.013890 0.025578 0.018025 15 0.450000 0.043554 -0.032219 0.026284 0.010239 16 0.500000 0.041555 -0.047827 0.026601 0.002430 17 0.550000 0.038841 -0.060871 0.026523 -0.005613 18 0.600000 0.035526 -0.072294 0.026032 -0.014148 19 0.650000 0.031702 -0.081457 0.025094 -0.023545 20 0.700000 0.027466 -0.087522 0.023653 -0.034437 21 0.750000 0.022978 -0.091265 0.021603 -0.048233 22 0.800000 0.018429 -0.090864 0.018694 -0.072138 23 0.850000 0.013875 -0.090860 0.014428 -0.093718 24 0.900000 0.009318 -0.093023 0.009808 -0.098084 25 0.950000 0.004726 -0.083274 0.004904 -0.098084 26 1.000000 0.000000 -4.794286 0.000000 -0.098084 COORDINATES OF NACA AIRFOILS 17:46 4Jan2002 NACA 63A409 COMBINED THICKNESS AND CAMBER xupper yupper xlower ylower 1 0.000000 0.000000 0.000000 0.000000 2 0.003604 0.008468 0.006396 -0.006219 3 0.005942 0.010435 0.009058 -0.007273 4 0.010724 0.013647 0.014276 -0.008822 5 0.022918 0.019802 0.027082 -0.011364 6 0.047648 0.028867 0.052352 -0.014442 7 0.072551 0.035921 0.077449 -0.016467 8 0.097538 0.041773 0.102462 -0.017932 9 0.147651 0.051101 0.152349 -0.019873 10 0.197872 0.058143 0.202128 -0.020939 11 0.248157 0.063409 0.251843 -0.021352 12 0.298481 0.067164 0.301519 -0.021221 13 0.348832 0.069423 0.351168 -0.020466 14 0.399194 0.070296 0.400806 -0.019141 15 0.449554 0.069835 0.450446 -0.017268 16 0.499899 0.068156 0.500101 -0.014953 17 0.550218 0.065364 0.549782 -0.012318 18 0.600503 0.061554 0.599497 -0.009491 19 0.650746 0.056787 0.649254 -0.006599 20 0.700945 0.051103 0.699055 -0.003798 21 0.751107 0.044555 0.748893 -0.001348 22 0.801326 0.037074 0.798674 0.000313 23 0.851295 0.028242 0.848705 0.000613 24 0.900910 0.019082 0.899090 0.000535 25 0.950461 0.009608 0.949539 0.000201 26 1.000000 0.000000 1.000000 0.000000 COORDINATES OF NACA AIRFOILS 17:46 4Jan2002 NACA 63A409 INTERPOLATED COORDINATES x yupper ylower 1 0.000000 0.000000 0.000000 2 0.005000 0.009709 -0.005499 3 0.007500 0.011556 -0.006697 4 0.012500 0.014692 -0.008344 5 0.025000 0.020691 -0.011027 6 0.050000 0.029600 -0.014214 7 0.075000 0.036541 -0.016298 8 0.100000 0.042300 -0.017806 9 0.150000 0.051476 -0.019804 10 0.200000 0.058400 -0.020908 11 0.250000 0.063573 -0.021347 12 0.300000 0.067253 -0.021234 13 0.350000 0.069458 -0.020491 14 0.400000 0.070299 -0.019167 15 0.450000 0.069826 -0.017287 16 0.500000 0.068151 -0.014959 17 0.550000 0.065378 -0.012306 18 0.600000 0.061597 -0.009462 19 0.650000 0.056864 -0.006556 20 0.700000 0.051218 -0.003747 21 0.750000 0.044708 -0.001300 22 0.800000 0.037291 0.000337 23 0.850000 0.028480 0.000613 24 0.900000 0.019253 0.000531 25 0.950000 0.009697 0.000198 26 1.000000 0.000000 0.000000 End of output for cambered airfoil