XFOIL Version 6.96 Calculated polar for: GOE 601 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 ------ -------- --------- --------- -------- -------- -------- -17.250 -0.7216 0.10208 0.09731 -0.0686 1.0000 0.0314 -17.000 -0.7645 0.09072 0.08568 -0.0753 1.0000 0.0314 -16.750 -0.7921 0.08280 0.07755 -0.0799 1.0000 0.0315 -16.500 -0.8163 0.07599 0.07052 -0.0837 1.0000 0.0317 -16.250 -0.8341 0.07061 0.06496 -0.0863 1.0000 0.0318 -16.000 -0.8377 0.06751 0.06184 -0.0871 1.0000 0.0322 -15.750 -0.8428 0.06434 0.05862 -0.0879 1.0000 0.0325 -15.500 -0.8482 0.06122 0.05544 -0.0887 1.0000 0.0328 -15.250 -0.8542 0.05814 0.05226 -0.0893 1.0000 0.0331 -15.000 -0.8598 0.05526 0.04931 -0.0897 1.0000 0.0335 -14.750 -0.8654 0.05248 0.04644 -0.0899 1.0000 0.0338 -14.500 -0.8708 0.04989 0.04375 -0.0898 1.0000 0.0343 -14.250 -0.8762 0.04744 0.04119 -0.0893 1.0000 0.0347 -14.000 -0.8816 0.04519 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0.750 0.3365 0.01171 0.00452 -0.0591 0.6998 0.6504 1.000 0.3610 0.01163 0.00449 -0.0582 0.6917 0.6712 1.250 0.3828 0.01157 0.00451 -0.0568 0.6819 0.6933 1.500 0.4065 0.01151 0.00453 -0.0558 0.6735 0.7171 1.750 0.4295 0.01146 0.00458 -0.0546 0.6645 0.7437 2.000 0.4534 0.01141 0.00464 -0.0535 0.6552 0.7734 2.250 0.4802 0.01138 0.00470 -0.0530 0.6446 0.8050 2.500 0.5091 0.01142 0.00483 -0.0530 0.6330 0.8377 2.750 0.5421 0.01149 0.00495 -0.0539 0.6200 0.8670 3.000 0.5783 0.01161 0.00506 -0.0555 0.6039 0.8891 3.250 0.6144 0.01176 0.00518 -0.0571 0.5854 0.9078 3.500 0.6497 0.01195 0.00531 -0.0587 0.5644 0.9247 3.750 0.6825 0.01218 0.00545 -0.0597 0.5389 0.9401 4.000 0.7127 0.01250 0.00563 -0.0603 0.5073 0.9541 4.250 0.7416 0.01291 0.00586 -0.0608 0.4684 0.9663 4.500 0.7676 0.01343 0.00616 -0.0609 0.4284 0.9790 4.750 0.7936 0.01402 0.00653 -0.0611 0.3909 0.9909 5.000 0.8189 0.01460 0.00693 -0.0613 0.3633 1.0000 5.250 0.8191 0.01490 0.00713 -0.0561 0.3494 1.0000 5.500 0.8207 0.01521 0.00735 -0.0512 0.3378 1.0000 5.750 0.8259 0.01554 0.00760 -0.0470 0.3273 1.0000 6.000 0.8345 0.01586 0.00788 -0.0435 0.3178 1.0000 6.250 0.8440 0.01623 0.00819 -0.0403 0.3095 1.0000 6.500 0.8561 0.01657 0.00851 -0.0376 0.3018 1.0000 6.750 0.8686 0.01693 0.00885 -0.0349 0.2942 1.0000 7.000 0.8812 0.01733 0.00921 -0.0324 0.2867 1.0000 7.250 0.8959 0.01767 0.00957 -0.0303 0.2795 1.0000 7.500 0.9092 0.01811 0.00998 -0.0280 0.2733 1.0000 7.750 0.9254 0.01846 0.01036 -0.0262 0.2677 1.0000 8.000 0.9410 0.01884 0.01077 -0.0243 0.2612 1.0000 8.250 0.9542 0.01933 0.01123 -0.0222 0.2539 1.0000 8.500 0.9704 0.01972 0.01168 -0.0205 0.2463 1.0000 8.750 0.9838 0.02023 0.01218 -0.0186 0.2393 1.0000 9.000 0.9997 0.02067 0.01267 -0.0170 0.2310 1.0000 9.250 1.0122 0.02126 0.01324 -0.0150 0.2224 1.0000 9.500 1.0277 0.02176 0.01379 -0.0135 0.2129 1.0000 9.750 1.0394 0.02243 0.01444 -0.0115 0.1984 1.0000 10.000 1.0504 0.02319 0.01516 -0.0096 0.1821 1.0000 10.250 1.0586 0.02415 0.01602 -0.0076 0.1599 1.0000 10.500 1.0626 0.02545 0.01712 -0.0052 0.1259 1.0000 10.750 1.0535 0.02772 0.01897 -0.0018 0.0740 1.0000 11.000 1.0559 0.02933 0.02048 0.0004 0.0573 1.0000 11.250 1.0620 0.03072 0.02185 0.0021 0.0503 1.0000 11.500 1.0704 0.03197 0.02313 0.0036 0.0472 1.0000 11.750 1.0771 0.03337 0.02457 0.0051 0.0447 1.0000 12.000 1.0838 0.03481 0.02607 0.0065 0.0432 1.0000 12.250 1.0908 0.03625 0.02760 0.0078 0.0419 1.0000 12.500 1.0969 0.03781 0.02925 0.0090 0.0410 1.0000 12.750 1.1017 0.03952 0.03104 0.0102 0.0398 1.0000 13.000 1.1046 0.04145 0.03305 0.0113 0.0389 1.0000 13.250 1.1061 0.04357 0.03524 0.0123 0.0383 1.0000 13.500 1.1046 0.04605 0.03779 0.0132 0.0375 1.0000 13.750 1.1071 0.04824 0.04009 0.0138 0.0370 1.0000 14.000 1.1087 0.05060 0.04255 0.0143 0.0364 1.0000 14.250 1.1091 0.05315 0.04520 0.0147 0.0360 1.0000 14.500 1.1087 0.05588 0.04803 0.0150 0.0354 1.0000 14.750 1.1084 0.05869 0.05093 0.0151 0.0351 1.0000 15.000 1.1072 0.06166 0.05398 0.0151 0.0345 1.0000 15.250 1.1061 0.06469 0.05710 0.0149 0.0342 1.0000 15.500 1.1049 0.06780 0.06029 0.0147 0.0338 1.0000 15.750 1.1035 0.07099 0.06354 0.0143 0.0333 1.0000 16.000 1.1019 0.07422 0.06683 0.0139 0.0328 1.0000 16.250 1.1011 0.07732 0.06996 0.0135 0.0324 1.0000 16.500 1.1017 0.08024 0.07291 0.0132 0.0319 1.0000 16.750 1.1039 0.08310 0.07587 0.0127 0.0316 1.0000 17.000 1.1061 0.08598 0.07885 0.0122 0.0312 1.0000 17.250 1.1081 0.08892 0.08189 0.0116 0.0308 1.0000 17.500 1.1107 0.09173 0.08479 0.0110 0.0304 1.0000