XFOIL Version 6.96 Calculated polar for: HQ 2.1/9.5 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.5865 0.05469 0.05304 -0.0547 1.0000 0.0116 -9.250 -0.6191 0.04861 0.04683 -0.0567 1.0000 0.0114 -9.000 -0.6940 0.02715 0.02405 -0.0586 0.9971 0.0115 -8.750 -0.6737 0.02112 0.01729 -0.0616 0.9930 0.0121 -8.500 -0.6438 0.01999 0.01606 -0.0631 0.9896 0.0125 -8.250 -0.6118 0.01912 0.01508 -0.0647 0.9868 0.0129 -8.000 -0.5789 0.01825 0.01411 -0.0665 0.9846 0.0134 -7.750 -0.5465 0.01730 0.01303 -0.0680 0.9820 0.0140 -7.500 -0.5164 0.01655 0.01215 -0.0689 0.9765 0.0146 -7.250 -0.4839 0.01567 0.01111 -0.0702 0.9724 0.0151 -7.000 -0.4523 0.01519 0.01052 -0.0712 0.9666 0.0153 -6.750 -0.4262 0.01283 0.00793 -0.0716 0.9583 0.0162 -6.500 -0.3985 0.01222 0.00727 -0.0718 0.9491 0.0168 -6.250 -0.3711 0.01179 0.00678 -0.0718 0.9396 0.0174 -6.000 -0.3448 0.01146 0.00640 -0.0715 0.9288 0.0182 -5.750 -0.3190 0.01098 0.00583 -0.0712 0.9187 0.0187 -5.500 -0.2930 0.01053 0.00530 -0.0708 0.9094 0.0192 -5.250 -0.2668 0.01017 0.00486 -0.0705 0.9000 0.0197 -5.000 -0.2401 0.00990 0.00452 -0.0702 0.8914 0.0200 -4.750 -0.2154 0.00907 0.00357 -0.0697 0.8827 0.0213 -4.500 -0.1885 0.00878 0.00326 -0.0696 0.8747 0.0226 -4.250 -0.1614 0.00857 0.00299 -0.0694 0.8673 0.0238 -4.000 -0.1340 0.00834 0.00272 -0.0693 0.8604 0.0249 -3.750 -0.1066 0.00818 0.00250 -0.0691 0.8533 0.0258 -3.500 -0.0795 0.00784 0.00211 -0.0690 0.8447 0.0291 -3.250 -0.0523 0.00770 0.00191 -0.0687 0.8353 0.0326 -3.000 -0.0249 0.00748 0.00171 -0.0686 0.8261 0.0421 -2.750 0.0024 0.00725 0.00154 -0.0685 0.8183 0.0654 -2.500 0.0297 0.00700 0.00141 -0.0684 0.8100 0.1036 -2.250 0.0569 0.00666 0.00127 -0.0685 0.8027 0.1731 -2.000 0.0829 0.00597 0.00109 -0.0685 0.7955 0.3372 -1.750 0.1093 0.00549 0.00102 -0.0685 0.7891 0.4777 -1.500 0.1369 0.00531 0.00098 -0.0685 0.7827 0.5332 -1.250 0.1644 0.00519 0.00097 -0.0684 0.7771 0.5856 -1.000 0.1923 0.00510 0.00099 -0.0683 0.7712 0.6237 -0.750 0.2204 0.00509 0.00099 -0.0682 0.7652 0.6452 -0.500 0.2483 0.00507 0.00100 -0.0681 0.7595 0.6681 -0.250 0.2763 0.00505 0.00103 -0.0681 0.7530 0.6917 0.000 0.3039 0.00506 0.00105 -0.0679 0.7468 0.7116 0.250 0.3321 0.00504 0.00106 -0.0678 0.7398 0.7236 0.500 0.3600 0.00507 0.00107 -0.0677 0.7327 0.7331 0.750 0.3882 0.00505 0.00109 -0.0677 0.7249 0.7420 1.000 0.4160 0.00509 0.00110 -0.0676 0.7164 0.7509 1.250 0.4439 0.00509 0.00113 -0.0675 0.7061 0.7600 1.500 0.4716 0.00510 0.00115 -0.0674 0.6942 0.7693 1.750 0.4988 0.00516 0.00118 -0.0671 0.6749 0.7795 2.000 0.5249 0.00525 0.00120 -0.0667 0.6375 0.7904 2.500 0.5712 0.00608 0.00146 -0.0649 0.4791 0.8152 2.750 0.5963 0.00636 0.00161 -0.0643 0.4373 0.8297 3.000 0.6217 0.00657 0.00175 -0.0639 0.4062 0.8453 3.250 0.6472 0.00675 0.00188 -0.0634 0.3804 0.8621 3.500 0.6726 0.00691 0.00202 -0.0629 0.3577 0.8804 3.750 0.6967 0.00709 0.00216 -0.0621 0.3295 0.9025 4.000 0.7201 0.00723 0.00229 -0.0612 0.3021 0.9400 4.250 0.7536 0.00746 0.00244 -0.0626 0.2739 1.0000 4.500 0.7793 0.00779 0.00263 -0.0623 0.2393 1.0000 4.750 0.8041 0.00820 0.00285 -0.0619 0.2005 1.0000 5.000 0.8281 0.00871 0.00314 -0.0614 0.1558 1.0000 5.250 0.8519 0.00924 0.00346 -0.0609 0.1174 1.0000 5.500 0.8766 0.00966 0.00376 -0.0605 0.0931 1.0000 5.750 0.9018 0.01002 0.00404 -0.0601 0.0773 1.0000 6.000 0.9270 0.01037 0.00433 -0.0597 0.0657 1.0000 6.250 0.9522 0.01071 0.00463 -0.0594 0.0565 1.0000 6.500 0.9772 0.01107 0.00494 -0.0590 0.0461 1.0000 6.750 1.0014 0.01153 0.00532 -0.0585 0.0339 1.0000 7.000 1.0254 0.01199 0.00573 -0.0579 0.0277 1.0000 7.250 1.0500 0.01238 0.00616 -0.0574 0.0254 1.0000 7.500 1.0744 0.01276 0.00655 -0.0569 0.0234 1.0000 7.750 1.0975 0.01330 0.00710 -0.0562 0.0213 1.0000 8.000 1.1205 0.01384 0.00771 -0.0555 0.0202 1.0000 8.250 1.1444 0.01424 0.00815 -0.0549 0.0195 1.0000 8.500 1.1678 0.01467 0.00862 -0.0543 0.0185 1.0000 8.750 1.1906 0.01514 0.00912 -0.0536 0.0176 1.0000 9.000 1.2117 0.01579 0.00980 -0.0527 0.0166 1.0000 9.250 1.2281 0.01691 0.01103 -0.0510 0.0155 1.0000 9.500 1.2508 0.01732 0.01149 -0.0503 0.0152 1.0000 9.750 1.2726 0.01780 0.01202 -0.0495 0.0147 1.0000 10.000 1.2936 0.01832 0.01259 -0.0486 0.0140 1.0000 10.250 1.3142 0.01884 0.01315 -0.0477 0.0133 1.0000 10.500 1.3334 0.01947 0.01382 -0.0466 0.0128 1.0000 10.750 1.3478 0.02047 0.01489 -0.0448 0.0122 1.0000 11.000 1.3569 0.02188 0.01642 -0.0423 0.0116 1.0000 11.250 1.3738 0.02244 0.01706 -0.0408 0.0113 1.0000 11.500 1.3869 0.02314 0.01783 -0.0387 0.0110 1.0000 11.750 1.3997 0.02381 0.01857 -0.0367 0.0107 1.0000 12.000 1.4110 0.02458 0.01942 -0.0345 0.0103 1.0000 12.250 1.4224 0.02536 0.02025 -0.0326 0.0100 1.0000 12.500 1.4340 0.02612 0.02108 -0.0308 0.0096 1.0000 12.750 1.4441 0.02703 0.02204 -0.0290 0.0093 1.0000 13.000 1.4474 0.02849 0.02358 -0.0266 0.0090 1.0000 13.250 1.4393 0.03098 0.02622 -0.0236 0.0087 1.0000 13.500 1.4393 0.03296 0.02834 -0.0217 0.0085 1.0000 13.750 1.4488 0.03416 0.02962 -0.0206 0.0084 1.0000 14.000 1.4501 0.03619 0.03177 -0.0192 0.0083 1.0000 14.250 1.4538 0.03807 0.03377 -0.0183 0.0081 1.0000 14.500 1.4539 0.04042 0.03624 -0.0174 0.0080 1.0000 14.750 1.4548 0.04281 0.03874 -0.0169 0.0078 1.0000 15.000 1.4534 0.04557 0.04162 -0.0166 0.0076 1.0000 15.250 1.4508 0.04864 0.04480 -0.0167 0.0075 1.0000 15.500 1.4444 0.05235 0.04865 -0.0172 0.0074 1.0000 15.750 1.4358 0.05664 0.05308 -0.0182 0.0073 1.0000 16.000 1.4297 0.06089 0.05745 -0.0198 0.0072 1.0000 16.250 1.4227 0.06564 0.06231 -0.0218 0.0071 1.0000 16.500 1.4150 0.07085 0.06764 -0.0244 0.0070 1.0000 16.750 1.3971 0.07818 0.07513 -0.0283 0.0070 1.0000 17.000 1.3810 0.08556 0.08266 -0.0325 0.0070 1.0000 17.250 1.3628 0.09360 0.09085 -0.0371 0.0069 1.0000 17.500 1.3382 0.10312 0.10053 -0.0426 0.0070 1.0000 17.750 1.3182 0.11198 0.10952 -0.0478 0.0069 1.0000 18.000 1.2911 0.12265 0.12036 -0.0542 0.0070 1.0000