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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9475 0.09968 0.09533 -0.0593 1.0000 0.0341 -19.500 -0.9604 0.09432 0.08991 -0.0620 1.0000 0.0345 -19.250 -0.9717 0.08925 0.08478 -0.0644 1.0000 0.0348 -19.000 -0.9821 0.08438 0.07983 -0.0668 1.0000 0.0353 -18.750 -0.9912 0.07980 0.07517 -0.0689 1.0000 0.0356 -18.500 -0.9988 0.07548 0.07077 -0.0708 1.0000 0.0362 -18.250 -1.0051 0.07145 0.06666 -0.0725 1.0000 0.0364 -18.000 -1.0102 0.06766 0.06279 -0.0741 1.0000 0.0371 -17.750 -1.0135 0.06417 0.05922 -0.0754 1.0000 0.0375 -17.500 -1.0158 0.06091 0.05587 -0.0766 1.0000 0.0379 -17.250 -1.0165 0.05793 0.05280 -0.0775 1.0000 0.0384 -17.000 -1.0199 0.05470 0.04952 -0.0785 1.0000 0.0389 -16.750 -1.0070 0.05120 0.04595 -0.0827 0.9984 0.0396 -16.500 -0.9924 0.04819 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3.000 0.6020 0.01002 0.00361 -0.0529 0.4910 0.6657 3.250 0.6239 0.01004 0.00368 -0.0517 0.4871 0.6740 3.500 0.6449 0.01008 0.00374 -0.0502 0.4834 0.6833 3.750 0.6643 0.01012 0.00379 -0.0485 0.4797 0.6917 4.000 0.6846 0.01016 0.00387 -0.0469 0.4761 0.7009 4.250 0.7056 0.01020 0.00395 -0.0456 0.4723 0.7103 4.500 0.7252 0.01026 0.00406 -0.0439 0.4679 0.7205 4.750 0.7447 0.01035 0.00415 -0.0422 0.4639 0.7301 5.000 0.7631 0.01044 0.00428 -0.0403 0.4597 0.7403 5.250 0.7836 0.01053 0.00441 -0.0389 0.4555 0.7511 5.500 0.8019 0.01062 0.00456 -0.0370 0.4505 0.7615 5.750 0.8191 0.01076 0.00470 -0.0350 0.4458 0.7721 6.000 0.8370 0.01088 0.00487 -0.0331 0.4414 0.7832 6.250 0.8559 0.01101 0.00504 -0.0314 0.4362 0.7941 6.500 0.8730 0.01115 0.00523 -0.0294 0.4310 0.8056 6.750 0.8883 0.01134 0.00542 -0.0271 0.4262 0.8162 7.000 0.9070 0.01148 0.00563 -0.0255 0.4214 0.8278 7.250 0.9238 0.01166 0.00585 -0.0235 0.4154 0.8393 7.500 0.9379 0.01191 0.00611 -0.0212 0.4098 0.8514 7.750 0.9569 0.01211 0.00636 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1.0000 13.250 1.3162 0.03516 0.02967 -0.0193 0.2353 1.0000 13.500 1.3158 0.03738 0.03188 -0.0184 0.2275 1.0000 13.750 1.3204 0.03923 0.03374 -0.0177 0.2206 1.0000 14.000 1.3216 0.04144 0.03595 -0.0170 0.2133 1.0000 14.250 1.3234 0.04360 0.03812 -0.0164 0.2055 1.0000 14.500 1.3242 0.04591 0.04042 -0.0158 0.1982 1.0000 14.750 1.3271 0.04808 0.04260 -0.0153 0.1920 1.0000 15.000 1.3282 0.05043 0.04495 -0.0148 0.1843 1.0000 15.250 1.3296 0.05280 0.04733 -0.0144 0.1783 1.0000 15.500 1.3301 0.05528 0.04981 -0.0141 0.1706 1.0000 15.750 1.3310 0.05778 0.05232 -0.0138 0.1650 1.0000 16.000 1.3311 0.06037 0.05491 -0.0136 0.1574 1.0000 16.250 1.3302 0.06310 0.05765 -0.0134 0.1512 1.0000 16.500 1.3309 0.06571 0.06026 -0.0133 0.1446 1.0000 16.750 1.3294 0.06858 0.06315 -0.0133 0.1387 1.0000 17.000 1.3292 0.07137 0.06594 -0.0133 0.1321 1.0000 17.250 1.3280 0.07426 0.06884 -0.0133 0.1269 1.0000 17.500 1.3277 0.07711 0.07172 -0.0135 0.1212 1.0000 17.750 1.3251 0.08025 0.07485 -0.0137 0.1158 1.0000 18.000 1.3236 0.08332 0.07795 -0.0140 0.1098 1.0000 18.250 1.3208 0.08654 0.08118 -0.0143 0.1052 1.0000 18.500 1.3199 0.08958 0.08426 -0.0147 0.1001 1.0000 18.750 1.3156 0.09306 0.08773 -0.0152 0.0952 1.0000 19.000 1.3139 0.09627 0.09098 -0.0158 0.0900 1.0000