XFOIL Version 6.96 Calculated polar for: GOE 491 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.000 -0.4491 0.09548 0.09196 -0.0077 1.0000 0.0239 -7.750 -0.4488 0.09279 0.08932 -0.0092 1.0000 0.0241 -7.500 -0.4504 0.09006 0.08665 -0.0111 1.0000 0.0244 -7.250 -0.4453 0.08689 0.08350 -0.0135 1.0000 0.0244 -7.000 -0.4386 0.08337 0.07998 -0.0167 1.0000 0.0246 -6.750 -0.4299 0.07974 0.07635 -0.0190 1.0000 0.0246 -6.500 -0.4197 0.07602 0.07262 -0.0211 1.0000 0.0247 -6.250 -0.4086 0.07216 0.06872 -0.0229 1.0000 0.0247 -5.750 -0.3921 0.06114 0.05765 -0.0242 1.0000 0.0139 -5.500 -0.3774 0.05847 0.05492 -0.0242 1.0000 0.0129 -5.250 -0.3649 0.05420 0.05057 -0.0252 1.0000 0.0125 -5.000 -0.3502 0.05013 0.04640 -0.0259 1.0000 0.0122 -4.750 -0.3342 0.04618 0.04233 -0.0262 1.0000 0.0120 -4.500 -0.3173 0.04218 0.03818 -0.0262 1.0000 0.0120 -4.250 -0.2998 0.03822 0.03402 -0.0257 1.0000 0.0121 -4.000 -0.2798 0.03520 0.03081 -0.0247 1.0000 0.0132 -3.750 -0.2627 0.03073 0.02606 -0.0235 0.9999 0.0135 -3.500 -0.2298 0.02416 0.01883 -0.0249 0.9955 0.0137 -3.250 -0.1993 0.01852 0.01225 -0.0252 0.9909 0.0141 -3.000 -0.1664 0.01540 0.00842 -0.0258 0.9871 0.0155 -2.750 -0.1332 0.01428 0.00704 -0.0267 0.9807 0.0191 -2.500 -0.0999 0.01314 0.00566 -0.0275 0.9737 0.0229 -2.250 -0.0656 0.01253 0.00502 -0.0287 0.9656 0.0312 -2.000 -0.0323 0.01237 0.00477 -0.0296 0.9561 0.0457 -1.750 -0.0001 0.01239 0.00468 -0.0305 0.9463 0.0570 -1.500 0.0356 0.01253 0.00473 -0.0321 0.9376 0.0682 -1.250 0.0713 0.01187 0.00404 -0.0337 0.9286 0.0715 -1.000 0.1069 0.01144 0.00359 -0.0352 0.9176 0.0745 -0.750 0.1438 0.01107 0.00318 -0.0370 0.9053 0.0780 -0.500 0.1804 0.01077 0.00281 -0.0387 0.8903 0.0816 -0.250 0.2150 0.01048 0.00252 -0.0400 0.8721 0.0871 0.000 0.2463 0.01032 0.00231 -0.0405 0.8493 0.0949 0.250 0.2755 0.01015 0.00212 -0.0406 0.8213 0.1045 0.500 0.3032 0.01003 0.00196 -0.0402 0.7878 0.1218 0.750 0.3282 0.00983 0.00187 -0.0394 0.7486 0.1933 1.250 0.4479 0.00847 0.00186 -0.0533 0.6366 1.0000 1.500 0.4690 0.00879 0.00188 -0.0517 0.5809 1.0000 1.750 0.4893 0.00918 0.00191 -0.0501 0.5181 1.0000 2.000 0.5104 0.00955 0.00198 -0.0486 0.4717 1.0000 2.250 0.5326 0.00986 0.00209 -0.0475 0.4394 1.0000 2.500 0.5560 0.01009 0.00223 -0.0465 0.4206 1.0000 2.750 0.5799 0.01029 0.00238 -0.0457 0.4061 1.0000 3.000 0.6039 0.01048 0.00254 -0.0449 0.3934 1.0000 3.250 0.6278 0.01067 0.00271 -0.0440 0.3785 1.0000 3.500 0.6518 0.01087 0.00292 -0.0432 0.3632 1.0000 3.750 0.6754 0.01109 0.00311 -0.0423 0.3425 1.0000 4.000 0.6986 0.01134 0.00330 -0.0414 0.3132 1.0000 4.250 0.7215 0.01164 0.00354 -0.0405 0.2773 1.0000 4.500 0.7437 0.01204 0.00380 -0.0394 0.2383 1.0000 4.750 0.7659 0.01246 0.00414 -0.0384 0.2042 1.0000 5.000 0.7874 0.01301 0.00455 -0.0373 0.1661 1.0000 5.250 0.8085 0.01362 0.00502 -0.0362 0.1233 1.0000 5.500 0.8277 0.01451 0.00566 -0.0348 0.0692 1.0000 5.750 0.8490 0.01512 0.00625 -0.0337 0.0553 1.0000 6.000 0.8706 0.01571 0.00689 -0.0325 0.0495 1.0000 6.250 0.8919 0.01630 0.00760 -0.0313 0.0440 1.0000 6.500 0.9115 0.01711 0.00849 -0.0300 0.0374 1.0000 6.750 0.9311 0.01790 0.00945 -0.0286 0.0317 1.0000 7.000 0.9498 0.01881 0.01051 -0.0271 0.0269 1.0000 7.250 0.9701 0.01952 0.01135 -0.0258 0.0204 1.0000 7.500 0.9859 0.02082 0.01275 -0.0239 0.0173 1.0000 7.750 1.0045 0.02179 0.01387 -0.0223 0.0146 1.0000 8.000 1.0235 0.02261 0.01480 -0.0210 0.0124 1.0000 8.250 1.0388 0.02402 0.01632 -0.0191 0.0111 1.0000 8.500 1.0489 0.02658 0.01907 -0.0165 0.0102 1.0000 8.750 1.0639 0.02846 0.02121 -0.0145 0.0097 1.0000 9.000 1.0785 0.03027 0.02337 -0.0127 0.0090 1.0000 9.250 1.0925 0.03180 0.02513 -0.0110 0.0081 1.0000 9.500 1.1041 0.03360 0.02717 -0.0091 0.0076 1.0000 9.750 1.1133 0.03551 0.02932 -0.0071 0.0072 1.0000 10.000 1.1184 0.03787 0.03193 -0.0047 0.0070 1.0000 10.250 1.1186 0.04061 0.03497 -0.0021 0.0068 1.0000 10.500 1.1121 0.04357 0.03820 0.0010 0.0067 1.0000 10.750 1.1018 0.04641 0.04129 0.0043 0.0067 1.0000 11.000 1.0853 0.05004 0.04518 0.0066 0.0066 1.0000 11.250 1.0689 0.05402 0.04938 0.0072 0.0066 1.0000 11.750 1.0414 0.06324 0.05903 0.0038 0.0066 1.0000 12.250 1.0121 0.07631 0.07248 -0.0052 0.0067 1.0000 12.500 0.9936 0.08480 0.08114 -0.0111 0.0068 1.0000 12.750 0.9594 0.09837 0.09493 -0.0199 0.0072 1.0000 13.000 0.9224 0.11426 0.11089 -0.0286 0.0076 1.0000