XFOIL Version 6.94 Calculated polar for: NACA 65(4)-221 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.1567 0.01229 0.00686 -0.0351 0.6413 0.6414 0.500 0.2128 0.01234 0.00692 -0.0359 0.6377 0.6444 1.000 0.2689 0.01241 0.00699 -0.0367 0.6338 0.6468 1.500 0.3251 0.01254 0.00712 -0.0374 0.6295 0.6488 2.000 0.3806 0.01231 0.00689 -0.0382 0.6252 0.6557 2.500 0.4365 0.01223 0.00684 -0.0390 0.6207 0.6631 3.000 0.4922 0.01230 0.00695 -0.0395 0.6158 0.6690 3.500 0.5475 0.01259 0.00729 -0.0401 0.6079 0.6745 4.000 0.5939 0.01343 0.00825 -0.0394 0.5995 0.6801 4.500 0.6515 0.01295 0.00783 -0.0398 0.5954 0.6856 5.000 0.7115 0.01196 0.00681 -0.0403 0.5806 0.6907 5.500 0.7666 0.01167 0.00659 -0.0403 0.5683 0.6949 6.000 0.8194 0.01174 0.00661 -0.0401 0.5494 0.6979 6.500 0.8573 0.01147 0.00648 -0.0371 0.5374 0.7044 7.000 0.8758 0.01128 0.00628 -0.0303 0.5106 0.7159 7.500 0.8773 0.01161 0.00668 -0.0207 0.4847 0.7253 8.000 0.8509 0.01272 0.00763 -0.0072 0.4328 0.7356 8.500 0.8067 0.01489 0.00952 0.0074 0.3699 0.7449 9.000 0.7651 0.01760 0.01198 0.0197 0.3123 0.7537 9.500 0.7282 0.02069 0.01494 0.0302 0.2571 0.7718 10.000 0.6978 0.02415 0.01821 0.0388 0.1992 0.7861 10.500 0.6751 0.02772 0.02158 0.0455 0.1420 0.7971 11.500 0.6429 0.03459 0.02807 0.0566 0.0464 0.8387 12.000 0.6569 0.03672 0.03033 0.0593 0.0412 0.8616 12.500 0.6673 0.03886 0.03268 0.0628 0.0373 0.8987 13.000 0.6966 0.04209 0.03614 0.0609 0.0322 0.9661 13.500 0.7103 0.04643 0.04068 0.0597 0.0282 1.0000 14.000 0.7170 0.04952 0.04395 0.0619 0.0256 1.0000 14.500 0.7303 0.05216 0.04686 0.0647 0.0231 1.0000 15.000 0.7520 0.05470 0.04948 0.0652 0.0228 1.0000 15.500 0.7726 0.05745 0.05242 0.0657 0.0225 1.0000 16.000 0.7900 0.06066 0.05578 0.0660 0.0221 1.0000 16.500 0.8018 0.06462 0.05993 0.0662 0.0218 1.0000 17.000 0.8006 0.07008 0.06563 0.0658 0.0216 1.0000 17.500 0.7952 0.07641 0.07223 0.0649 0.0214 1.0000 18.000 0.7767 0.08475 0.08087 0.0630 0.0214 1.0000 18.500 0.7489 0.09493 0.09135 0.0597 0.0215 1.0000 19.000 0.7034 0.10856 0.10531 0.0539 0.0216 1.0000 19.500 0.6026 0.13430 0.13149 0.0412 0.0222 1.0000