XFOIL Version 6.96 Calculated polar for: AH 93-W-215 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1266 0.07523 0.07113 -0.0695 1.0000 0.0276 -19.500 -1.1376 0.07065 0.06646 -0.0715 1.0000 0.0279 -19.250 -1.1460 0.06651 0.06224 -0.0732 1.0000 0.0282 -19.000 -1.1462 0.06249 0.05814 -0.0761 0.9996 0.0286 -18.750 -1.1384 0.05868 0.05425 -0.0800 0.9986 0.0291 -18.500 -1.1272 0.05510 0.05059 -0.0842 0.9968 0.0294 -18.250 -1.1163 0.05222 0.04763 -0.0869 0.9945 0.0300 -18.000 -1.1178 0.04909 0.04444 -0.0878 0.9917 0.0304 -17.750 -1.1177 0.04624 0.04154 -0.0886 0.9881 0.0309 -17.500 -1.0853 0.04296 0.03817 -0.0957 0.9290 0.0316 -17.250 -1.0118 0.04010 0.03469 -0.1104 0.7939 0.0329 -17.000 -1.0028 0.03838 0.03279 -0.1112 0.7599 0.0334 -16.750 -0.9935 0.03670 0.03098 -0.1118 0.7403 0.0339 -16.500 -0.9847 0.03499 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3.000 0.6037 0.00799 0.00243 -0.0526 0.4643 0.6180 3.250 0.6256 0.00806 0.00248 -0.0514 0.4602 0.6244 3.500 0.6489 0.00808 0.00254 -0.0505 0.4568 0.6326 3.750 0.6719 0.00813 0.00261 -0.0495 0.4522 0.6404 4.000 0.6938 0.00820 0.00269 -0.0482 0.4477 0.6481 4.250 0.7140 0.00829 0.00279 -0.0467 0.4428 0.6572 4.500 0.7375 0.00835 0.00287 -0.0458 0.4392 0.6653 4.750 0.7587 0.00842 0.00297 -0.0445 0.4337 0.6742 5.000 0.7780 0.00854 0.00309 -0.0428 0.4282 0.6835 5.250 0.7982 0.00864 0.00321 -0.0413 0.4236 0.6925 5.500 0.8192 0.00872 0.00333 -0.0400 0.4186 0.7032 5.750 0.8385 0.00885 0.00347 -0.0383 0.4130 0.7122 6.000 0.8571 0.00899 0.00362 -0.0366 0.4077 0.7233 6.250 0.8777 0.00909 0.00376 -0.0352 0.4025 0.7338 6.500 0.8955 0.00925 0.00394 -0.0333 0.3954 0.7454 6.750 0.9128 0.00942 0.00412 -0.0314 0.3900 0.7558 7.000 0.9316 0.00957 0.00430 -0.0298 0.3835 0.7677 7.250 0.9481 0.00977 0.00453 -0.0278 0.3769 0.7782 7.500 0.9662 0.00996 0.00474 -0.0261 0.3715 0.7904 7.750 0.9837 0.01017 0.00498 -0.0243 0.3644 0.8013 8.000 0.9994 0.01046 0.00527 -0.0224 0.3579 0.8129 8.250 1.0191 0.01066 0.00553 -0.0212 0.3525 0.8244 8.500 1.0373 0.01096 0.00584 -0.0198 0.3454 0.8348 8.750 1.0556 0.01132 0.00622 -0.0186 0.3383 0.8460 9.000 1.0768 0.01167 0.00659 -0.0181 0.3301 0.8562 9.250 1.0981 0.01215 0.00708 -0.0178 0.3216 0.8681 9.500 1.1262 0.01259 0.00755 -0.0189 0.3131 0.8792 9.750 1.1545 0.01314 0.00811 -0.0203 0.3060 0.8900 10.000 1.1900 0.01361 0.00862 -0.0230 0.2988 0.9000 10.250 1.2252 0.01437 0.00937 -0.0262 0.2880 0.9093 10.500 1.2564 0.01514 0.01016 -0.0287 0.2776 0.9216 10.750 1.2876 0.01595 0.01099 -0.0312 0.2684 0.9374 11.000 1.3202 0.01704 0.01208 -0.0346 0.2575 0.9577 11.500 1.3460 0.01976 0.01477 -0.0339 0.2383 1.0000 11.750 1.3503 0.02139 0.01638 -0.0325 0.2284 1.0000 12.000 1.3578 0.02285 0.01784 -0.0315 0.2212 1.0000 12.250 1.3606 0.02466 0.01964 -0.0303 0.2124 1.0000 12.500 1.3666 0.02627 0.02125 -0.0293 0.2058 1.0000 12.750 1.3707 0.02803 0.02301 -0.0283 0.1992 1.0000 13.000 1.3717 0.03001 0.02498 -0.0271 0.1910 1.0000 13.250 1.3744 0.03188 0.02685 -0.0260 0.1844 1.0000 13.500 1.3761 0.03386 0.02882 -0.0250 0.1775 1.0000 13.750 1.3777 0.03589 0.03086 -0.0240 0.1711 1.0000 14.000 1.3785 0.03802 0.03298 -0.0231 0.1640 1.0000 14.250 1.3799 0.04017 0.03513 -0.0223 0.1573 1.0000 14.500 1.3801 0.04246 0.03741 -0.0215 0.1506 1.0000 14.750 1.3800 0.04479 0.03973 -0.0208 0.1431 1.0000 15.000 1.3813 0.04708 0.04203 -0.0202 0.1371 1.0000 15.250 1.3825 0.04940 0.04434 -0.0197 0.1308 1.0000 15.500 1.3826 0.05186 0.04680 -0.0192 0.1246 1.0000 15.750 1.3824 0.05436 0.04929 -0.0187 0.1182 1.0000 16.000 1.3824 0.05692 0.05185 -0.0184 0.1122 1.0000 16.250 1.3830 0.05944 0.05437 -0.0181 0.1072 1.0000 16.500 1.3829 0.06205 0.05699 -0.0178 0.1014 1.0000 16.750 1.3817 0.06482 0.05976 -0.0176 0.0962 1.0000 17.000 1.3831 0.06735 0.06230 -0.0176 0.0916 1.0000 17.250 1.3781 0.07062 0.06556 -0.0175 0.0849 1.0000 17.500 1.3792 0.07324 0.06819 -0.0175 0.0807 1.0000 17.750 1.3763 0.07634 0.07130 -0.0176 0.0765 1.0000 18.000 1.3797 0.07876 0.07375 -0.0177 0.0741 1.0000 18.250 1.3753 0.08214 0.07715 -0.0179 0.0699 1.0000 18.500 1.3762 0.08490 0.07993 -0.0182 0.0663 1.0000