Selig airfoil for Q-500 (Q500) pylon racing (12.33%)
s8064 Airfoil (x,y) Co-ordinates
| 1 | 0 |
| 0.997927 | 0.000125 |
| 0.991844 | 0.000661 |
| 0.98195 | 0.001759 |
| 0.968438 | 0.003565 |
| 0.951588 | 0.006193 |
| 0.931716 | 0.009686 |
| 0.909164 | 0.014035 |
| 0.884293 | 0.019168 |
| 0.857469 | 0.024954 |
| 0.829053 | 0.031198 |
| 0.79939 | 0.03763 |
| 0.768826 | 0.04376 |
| 0.737098 | 0.049161 |
| 0.703928 | 0.053909 |
| 0.669588 | 0.05818 |
| 0.634301 | 0.061961 |
| 0.598271 | 0.065229 |
| 0.561701 | 0.067947 |
| 0.524799 | 0.070079 |
| 0.487769 | 0.071601 |
| 0.450799 | 0.0725 |
| 0.414069 | 0.072755 |
| 0.37777 | 0.072374 |
| 0.342087 | 0.071387 |
| 0.307218 | 0.069831 |
| 0.273369 | 0.067736 |
| 0.240738 | 0.065134 |
| 0.209521 | 0.062054 |
| 0.1799 | 0.058531 |
| 0.15205 | 0.0546 |
| 0.126136 | 0.050302 |
| 0.102312 | 0.045678 |
| 0.080718 | 0.040772 |
| 0.061481 | 0.035636 |
| 0.044723 | 0.030322 |
| 0.030576 | 0.024873 |
| 0.019091 | 0.01931 |
| 0.010271 | 0.01367 |
| 0.004145 | 0.008047 |
| 0.000637 | 0.002692 |
| 0.000328 | -0.001911 |
| 0.003568 | -0.006325 |
| 0.009851 | -0.011082 |
| 0.018933 | -0.015812 |
| 0.030792 | -0.020402 |
| 0.045404 | -0.024768 |
| 0.062686 | -0.02886 |
| 0.082555 | -0.032657 |
| 0.104908 | -0.036143 |
| 0.12962 | -0.039299 |
| 0.156536 | -0.042118 |
| 0.185485 | -0.044585 |
| 0.216282 | -0.046683 |
| 0.248732 | -0.048388 |
| 0.282633 | -0.04968 |
| 0.317775 | -0.05053 |
| 0.353959 | -0.050905 |
| 0.390991 | -0.050795 |
| 0.428663 | -0.050184 |
| 0.466779 | -0.049071 |
| 0.505162 | -0.047491 |
| 0.543597 | -0.045496 |
| 0.581815 | -0.043133 |
| 0.619551 | -0.040409 |
| 0.656518 | -0.03728 |
| 0.69267 | -0.033539 |
| 0.728117 | -0.029328 |
| 0.762681 | -0.025064 |
| 0.796024 | -0.020943 |
| 0.827817 | -0.017097 |
| 0.857738 | -0.013617 |
| 0.885475 | -0.010558 |
| 0.91073 | -0.007944 |
| 0.933228 | -0.005769 |
| 0.952715 | -0.003991 |
| 0.969006 | -0.002502 |
| 0.982067 | -0.001257 |
| 0.99181 | -0.000404 |
| 0.997911 | -0.000042 |
| 1 | 0 |
s8064 Airfoil CAD files