XFOIL Version 6.94 Calculated polar for: HQ 2.5/9.0 smoothed by Eppler 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3627 0.00817 0.00340 -0.0823 0.8494 0.8359 0.500 0.4141 0.00809 0.00335 -0.0808 0.8352 0.8644 1.000 0.4639 0.00796 0.00327 -0.0789 0.8201 0.8992 1.500 0.5205 0.00773 0.00313 -0.0784 0.8036 0.9516 2.000 0.5884 0.00769 0.00304 -0.0809 0.7835 1.0000 2.500 0.6440 0.00776 0.00306 -0.0807 0.7575 1.0000 3.000 0.6971 0.00783 0.00302 -0.0796 0.7150 1.0000 3.500 0.7453 0.00808 0.00297 -0.0775 0.6157 1.0000 4.000 0.7870 0.00917 0.00335 -0.0748 0.4773 1.0000 4.500 0.8340 0.01010 0.00396 -0.0733 0.4088 1.0000 5.000 0.8814 0.01098 0.00461 -0.0720 0.3465 1.0000 5.500 0.9286 0.01184 0.00524 -0.0707 0.2789 1.0000 6.000 0.9723 0.01310 0.00606 -0.0690 0.1792 1.0000 6.500 1.0128 0.01482 0.00736 -0.0669 0.1021 1.0000 7.000 1.0545 0.01641 0.00882 -0.0648 0.0667 1.0000 7.500 1.0899 0.01869 0.01110 -0.0617 0.0476 1.0000 8.000 1.1319 0.02013 0.01272 -0.0595 0.0413 1.0000 8.500 1.1638 0.02315 0.01583 -0.0562 0.0357 1.0000 9.000 1.2042 0.02467 0.01760 -0.0539 0.0321 1.0000 9.500 1.2394 0.02688 0.02000 -0.0512 0.0285 1.0000 10.500 1.2953 0.03406 0.02790 -0.0445 0.0224 1.0000 11.000 1.3097 0.03737 0.03152 -0.0397 0.0206 1.0000 11.500 1.3101 0.04289 0.03742 -0.0347 0.0190 1.0000 12.000 1.2862 0.04992 0.04507 -0.0292 0.0182 1.0000 12.500 1.2675 0.05597 0.05159 -0.0263 0.0175 1.0000 13.000 1.2365 0.06486 0.06095 -0.0262 0.0172 1.0000 13.500 1.1964 0.07681 0.07334 -0.0302 0.0172 1.0000 14.000 1.1488 0.09318 0.09010 -0.0398 0.0175 1.0000 14.500 1.0855 0.11717 0.11436 -0.0554 0.0184 1.0000 16.500 0.7829 0.19711 0.19495 -0.0978 0.0351 1.0000 17.000 0.7811 0.20615 0.20399 -0.1045 0.0305 1.0000 17.500 0.7911 0.21365 0.21151 -0.1079 0.0283 1.0000