XFOIL Version 6.96 Calculated polar for: MH 94 16.03% 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 -0.7766 0.14044 0.13685 -0.0362 1.0000 0.0081 -19.500 -0.7943 0.13272 0.12900 -0.0402 1.0000 0.0081 -19.250 -0.8115 0.12538 0.12151 -0.0438 1.0000 0.0080 -19.000 -0.8257 0.11887 0.11489 -0.0470 1.0000 0.0080 -18.750 -0.8392 0.11266 0.10857 -0.0500 1.0000 0.0080 -18.500 -0.8507 0.10694 0.10273 -0.0526 1.0000 0.0080 -18.250 -0.8607 0.10162 0.09732 -0.0550 1.0000 0.0080 -18.000 -0.8725 0.09615 0.09174 -0.0574 1.0000 0.0080 -17.750 -0.8810 0.09135 0.08684 -0.0594 1.0000 0.0080 -17.500 -0.8910 0.08645 0.08185 -0.0614 1.0000 0.0081 -17.250 -0.8995 0.08189 0.07720 -0.0632 1.0000 0.0081 -17.000 -0.9061 0.07776 0.07297 -0.0646 1.0000 0.0081 -16.750 -0.9130 0.07371 0.06882 -0.0659 1.0000 0.0081 -16.500 -0.9189 0.06990 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0.6793 2.750 0.4878 0.01014 0.00313 -0.0395 0.3110 0.6865 3.000 0.5112 0.01035 0.00328 -0.0386 0.2907 0.6936 3.500 0.5586 0.01079 0.00358 -0.0370 0.2541 0.7078 3.750 0.5822 0.01099 0.00375 -0.0362 0.2389 0.7149 4.000 0.6059 0.01120 0.00391 -0.0355 0.2242 0.7223 4.250 0.6292 0.01142 0.00409 -0.0346 0.2093 0.7290 4.500 0.6521 0.01165 0.00428 -0.0337 0.1954 0.7363 4.750 0.6749 0.01190 0.00447 -0.0328 0.1823 0.7437 5.000 0.6968 0.01213 0.00467 -0.0317 0.1702 0.7504 5.250 0.7185 0.01236 0.00488 -0.0305 0.1589 0.7580 5.750 0.7608 0.01285 0.00532 -0.0281 0.1389 0.7724 6.000 0.7814 0.01313 0.00557 -0.0268 0.1299 0.7805 6.250 0.8027 0.01338 0.00582 -0.0256 0.1234 0.7877 6.500 0.8230 0.01366 0.00610 -0.0243 0.1171 0.7958 7.000 0.8643 0.01419 0.00667 -0.0218 0.1079 0.8121 7.250 0.8842 0.01451 0.00698 -0.0204 0.1040 0.8209 7.500 0.9044 0.01476 0.00729 -0.0191 0.1009 0.8293 7.750 0.9239 0.01506 0.00761 -0.0177 0.0976 0.8391 8.000 0.9423 0.01539 0.00796 -0.0162 0.0948 0.8486 8.250 0.9613 0.01569 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1.0000 13.500 1.2984 0.02810 0.02158 0.0119 0.0674 1.0000 13.750 1.3064 0.02935 0.02287 0.0132 0.0666 1.0000 14.000 1.3187 0.03036 0.02396 0.0141 0.0660 1.0000 14.250 1.3294 0.03150 0.02518 0.0150 0.0654 1.0000 14.500 1.3394 0.03273 0.02649 0.0159 0.0648 1.0000 14.750 1.3486 0.03407 0.02790 0.0167 0.0641 1.0000 15.000 1.3575 0.03547 0.02937 0.0174 0.0635 1.0000 15.250 1.3656 0.03697 0.03095 0.0180 0.0629 1.0000 15.500 1.3730 0.03860 0.03264 0.0186 0.0623 1.0000 15.750 1.3792 0.04037 0.03447 0.0190 0.0617 1.0000 16.000 1.3847 0.04227 0.03643 0.0193 0.0610 1.0000 16.250 1.3885 0.04440 0.03862 0.0194 0.0604 1.0000 16.500 1.3913 0.04671 0.04099 0.0195 0.0599 1.0000 16.750 1.3925 0.04923 0.04357 0.0194 0.0593 1.0000 17.000 1.3973 0.05148 0.04593 0.0192 0.0589 1.0000 17.250 1.4010 0.05391 0.04846 0.0189 0.0585 1.0000 17.500 1.4042 0.05646 0.05112 0.0184 0.0579 1.0000 17.750 1.4063 0.05920 0.05396 0.0177 0.0573 1.0000 18.000 1.4074 0.06212 0.05697 0.0169 0.0568 1.0000 18.250 1.4077 0.06522 0.06017 0.0160 0.0563 1.0000 18.500 1.4075 0.06847 0.06352 0.0148 0.0557 1.0000 18.750 1.4061 0.07195 0.06709 0.0135 0.0552 1.0000 19.000 1.4035 0.07564 0.07087 0.0120 0.0547 1.0000 19.250 1.4001 0.07953 0.07484 0.0104 0.0542 1.0000