XFOIL Version 6.96 Calculated polar for: RAF 31 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.500 -0.8513 0.11092 0.10873 -0.0361 1.0000 0.0158 -17.250 -0.9059 0.09604 0.09363 -0.0447 1.0000 0.0158 -17.000 -0.9326 0.08718 0.08466 -0.0499 1.0000 0.0159 -16.750 -0.9651 0.07771 0.07503 -0.0556 1.0000 0.0159 -16.500 -0.9854 0.07081 0.06801 -0.0598 1.0000 0.0159 -16.250 -1.0010 0.06489 0.06199 -0.0634 1.0000 0.0160 -16.000 -1.0133 0.05961 0.05661 -0.0666 1.0000 0.0161 -15.750 -1.0223 0.05489 0.05180 -0.0695 1.0000 0.0162 -15.500 -1.0257 0.05108 0.04793 -0.0719 1.0000 0.0163 -15.250 -1.0311 0.04716 0.04390 -0.0742 1.0000 0.0164 -15.000 -1.0332 0.04386 0.04052 -0.0761 1.0000 0.0166 -14.750 -1.0327 0.04106 0.03765 -0.0775 1.0000 0.0167 -14.500 -1.0348 0.03818 0.03467 -0.0787 1.0000 0.0169 -14.250 -1.0340 0.03587 0.03227 -0.0793 1.0000 0.0171 -14.000 -1.0292 0.03425 0.03059 -0.0794 1.0000 0.0174 -13.750 -1.0295 0.03236 0.02859 -0.0790 1.0000 0.0176 -13.500 -1.0264 0.03108 0.02725 -0.0779 1.0000 0.0179 -13.250 -1.0321 0.02928 0.02532 -0.0756 1.0000 0.0180 -13.000 -1.0308 0.02849 0.02446 -0.0728 1.0000 0.0182 -12.750 -1.0317 0.02796 0.02386 -0.0690 1.0000 0.0185 -12.500 -1.0301 0.02733 0.02314 -0.0653 1.0000 0.0187 -12.250 -1.0223 0.02678 0.02251 -0.0626 1.0000 0.0189 -12.000 -1.0139 0.02628 0.02193 -0.0599 1.0000 0.0191 -11.750 -1.0187 0.02392 0.01943 -0.0560 0.9998 0.0196 -11.500 -0.9899 0.02288 0.01836 -0.0576 0.9982 0.0200 -11.250 -0.9587 0.02229 0.01775 -0.0593 0.9962 0.0205 -11.000 -0.9275 0.02160 0.01700 -0.0610 0.9942 0.0210 -10.750 -0.8987 0.02099 0.01633 -0.0620 0.9913 0.0215 -10.500 -0.8690 0.02034 0.01561 -0.0631 0.9880 0.0221 -10.250 -0.8384 0.01959 0.01479 -0.0644 0.9852 0.0226 -10.000 -0.8077 0.01908 0.01420 -0.0656 0.9821 0.0230 -9.750 -0.7802 0.01869 0.01373 -0.0659 0.9757 0.0233 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0.0347 -4.750 -0.2221 0.00892 0.00283 -0.0719 0.8325 0.0364 -4.500 -0.1970 0.00873 0.00261 -0.0713 0.8234 0.0385 -4.250 -0.1718 0.00855 0.00241 -0.0707 0.8143 0.0414 -4.000 -0.1481 0.00825 0.00222 -0.0698 0.8046 0.0689 -3.750 -0.1227 0.00808 0.00208 -0.0693 0.7951 0.0841 -3.500 -0.0974 0.00792 0.00194 -0.0688 0.7863 0.0982 -3.250 -0.0727 0.00770 0.00179 -0.0681 0.7767 0.1229 -3.000 -0.0495 0.00734 0.00164 -0.0673 0.7680 0.1829 -2.750 -0.0250 0.00712 0.00152 -0.0666 0.7594 0.2215 -2.500 -0.0007 0.00687 0.00142 -0.0659 0.7506 0.2697 -2.250 0.0236 0.00669 0.00135 -0.0652 0.7414 0.3169 -2.000 0.0494 0.00655 0.00130 -0.0648 0.7334 0.3511 -1.750 0.0750 0.00645 0.00126 -0.0643 0.7263 0.3817 -1.500 0.1014 0.00636 0.00123 -0.0639 0.7196 0.4068 -1.250 0.1272 0.00626 0.00120 -0.0635 0.7127 0.4362 -1.000 0.1530 0.00615 0.00118 -0.0630 0.7064 0.4682 -0.750 0.1787 0.00605 0.00117 -0.0625 0.6993 0.5033 -0.500 0.2043 0.00598 0.00117 -0.0620 0.6923 0.5356 -0.250 0.2302 0.00590 0.00118 -0.0615 0.6849 0.5690 0.000 0.2558 0.00587 0.00119 -0.0609 0.6776 0.5978 0.250 0.2823 0.00582 0.00120 -0.0605 0.6703 0.6189 0.500 0.3081 0.00580 0.00122 -0.0600 0.6630 0.6404 0.750 0.3345 0.00577 0.00124 -0.0596 0.6556 0.6612 1.250 0.3854 0.00572 0.00130 -0.0584 0.6377 0.7130 1.500 0.4101 0.00570 0.00135 -0.0576 0.6284 0.7418 1.750 0.4342 0.00570 0.00139 -0.0566 0.6141 0.7690 2.000 0.4582 0.00572 0.00143 -0.0557 0.5961 0.7929 2.250 0.4815 0.00577 0.00148 -0.0546 0.5728 0.8155 2.500 0.5039 0.00585 0.00154 -0.0533 0.5441 0.8391 2.750 0.5248 0.00600 0.00163 -0.0518 0.5065 0.8669 3.000 0.5493 0.00617 0.00177 -0.0510 0.4727 0.9036 3.500 0.6488 0.00668 0.00216 -0.0610 0.4272 0.9582 3.750 0.6890 0.00687 0.00231 -0.0637 0.4136 0.9731 4.000 0.7225 0.00705 0.00245 -0.0650 0.4001 0.9855 4.250 0.7579 0.00725 0.00260 -0.0667 0.3834 0.9931 4.500 0.7952 0.00748 0.00274 -0.0690 0.3561 0.9980 4.750 0.8208 0.00806 0.00297 -0.0690 0.2858 1.0000 5.000 0.8383 0.00841 0.00320 -0.0669 0.2635 1.0000 5.250 0.8574 0.00869 0.00341 -0.0652 0.2469 1.0000 5.500 0.8764 0.00898 0.00362 -0.0635 0.2259 1.0000 5.750 0.8899 0.00958 0.00391 -0.0608 0.1667 1.0000 6.000 0.9036 0.01017 0.00429 -0.0581 0.1285 1.0000 6.250 0.9214 0.01055 0.00458 -0.0562 0.1106 1.0000 6.500 0.9404 0.01088 0.00485 -0.0545 0.0995 1.0000 6.750 0.9606 0.01114 0.00510 -0.0530 0.0918 1.0000 7.000 0.9798 0.01147 0.00537 -0.0514 0.0838 1.0000 7.250 1.0006 0.01170 0.00561 -0.0501 0.0800 1.0000 7.500 1.0199 0.01201 0.00589 -0.0485 0.0747 1.0000 7.750 1.0399 0.01227 0.00616 -0.0470 0.0708 1.0000 8.000 1.0599 0.01253 0.00642 -0.0456 0.0669 1.0000 8.250 1.0783 0.01287 0.00672 -0.0439 0.0623 1.0000 8.500 1.0980 0.01313 0.00700 -0.0424 0.0594 1.0000 8.750 1.1165 0.01342 0.00729 -0.0407 0.0561 1.0000 9.000 1.1315 0.01377 0.00762 -0.0384 0.0515 1.0000 9.250 1.1485 0.01405 0.00790 -0.0364 0.0474 1.0000 9.500 1.1624 0.01448 0.00829 -0.0340 0.0390 1.0000 9.750 1.1724 0.01515 0.00884 -0.0310 0.0261 1.0000 10.000 1.1834 0.01582 0.00946 -0.0283 0.0206 1.0000 10.250 1.1973 0.01638 0.01004 -0.0262 0.0186 1.0000 10.500 1.2103 0.01701 0.01070 -0.0240 0.0173 1.0000 10.750 1.2229 0.01770 0.01142 -0.0218 0.0161 1.0000 11.000 1.2374 0.01829 0.01207 -0.0200 0.0155 1.0000 11.250 1.2511 0.01897 0.01279 -0.0182 0.0150 1.0000 11.500 1.2644 0.01968 0.01355 -0.0165 0.0145 1.0000 11.750 1.2759 0.02054 0.01445 -0.0146 0.0139 1.0000 12.000 1.2816 0.02183 0.01581 -0.0122 0.0130 1.0000 12.250 1.2946 0.02265 0.01669 -0.0108 0.0128 1.0000 12.500 1.3069 0.02354 0.01764 -0.0094 0.0125 1.0000 12.750 1.3176 0.02458 0.01874 -0.0079 0.0122 1.0000 13.000 1.3284 0.02564 0.01986 -0.0065 0.0118 1.0000 13.250 1.3367 0.02691 0.02120 -0.0050 0.0116 1.0000 13.500 1.3451 0.02821 0.02257 -0.0037 0.0114 1.0000 13.750 1.3529 0.02961 0.02402 -0.0024 0.0111 1.0000 14.000 1.3553 0.03149 0.02597 -0.0010 0.0107 1.0000 14.250 1.3518 0.03397 0.02855 0.0005 0.0104 1.0000 14.500 1.3505 0.03635 0.03103 0.0016 0.0103 1.0000 14.750 1.3554 0.03825 0.03301 0.0023 0.0102 1.0000 15.000 1.3653 0.03972 0.03455 0.0028 0.0100 1.0000 15.250 1.3651 0.04220 0.03713 0.0034 0.0100 1.0000 15.500 1.3654 0.04473 0.03975 0.0038 0.0099 1.0000 15.750 1.3667 0.04727 0.04239 0.0040 0.0097 1.0000 16.000 1.3666 0.05004 0.04525 0.0041 0.0096 1.0000 16.250 1.3686 0.05264 0.04794 0.0040 0.0093 1.0000 16.500 1.3637 0.05616 0.05156 0.0036 0.0093 1.0000 16.750 1.3625 0.05936 0.05485 0.0031 0.0091 1.0000 17.000 1.3588 0.06296 0.05854 0.0024 0.0090 1.0000 17.250 1.3533 0.06690 0.06257 0.0015 0.0089 1.0000 17.500 1.3456 0.07129 0.06707 0.0002 0.0089 1.0000 17.750 1.3390 0.07564 0.07152 -0.0012 0.0088 1.0000 18.000 1.3334 0.07994 0.07590 -0.0027 0.0086 1.0000 18.250 1.3232 0.08496 0.08102 -0.0044 0.0086 1.0000 18.500 1.3146 0.08984 0.08599 -0.0063 0.0085 1.0000 18.750 1.3000 0.09570 0.09195 -0.0086 0.0084 1.0000 19.000 1.2890 0.10107 0.09742 -0.0108 0.0084 1.0000