XFOIL Version 6.96 Calculated polar for: WHITCOMB INTEGRAL SUPERCRITICAL 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.000 -1.0902 0.10811 0.10502 -0.0412 1.0000 0.0156 -18.750 -1.1234 0.09847 0.09523 -0.0463 1.0000 0.0156 -18.500 -1.1543 0.08933 0.08595 -0.0511 1.0000 0.0155 -18.250 -1.1829 0.08076 0.07723 -0.0557 1.0000 0.0155 -18.000 -1.2067 0.07318 0.06951 -0.0597 1.0000 0.0155 -17.750 -1.2267 0.06656 0.06274 -0.0631 1.0000 0.0156 -17.500 -1.2430 0.06083 0.05689 -0.0657 1.0000 0.0156 -17.250 -1.2563 0.05596 0.05189 -0.0676 1.0000 0.0157 -17.000 -1.2672 0.05175 0.04758 -0.0688 1.0000 0.0157 -16.750 -1.2752 0.04825 0.04397 -0.0694 1.0000 0.0158 -16.500 -1.2818 0.04516 0.04080 -0.0695 1.0000 0.0159 -16.250 -1.2865 0.04253 0.03808 -0.0691 1.0000 0.0159 -16.000 -1.2900 0.04022 0.03570 -0.0683 1.0000 0.0160 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-0.4395 0.01127 0.00564 -0.0919 0.9673 0.0397 -6.250 -0.4085 0.01104 0.00542 -0.0928 0.9666 0.0417 -6.000 -0.3769 0.01080 0.00520 -0.0939 0.9660 0.0443 -5.750 -0.3451 0.01059 0.00501 -0.0950 0.9654 0.0469 -5.500 -0.3129 0.01035 0.00482 -0.0962 0.9649 0.0516 -5.250 -0.2804 0.01012 0.00465 -0.0975 0.9645 0.0587 -5.000 -0.2476 0.00988 0.00448 -0.0988 0.9642 0.0681 -4.750 -0.2147 0.00967 0.00433 -0.1001 0.9638 0.0769 -4.500 -0.1817 0.00947 0.00419 -0.1015 0.9635 0.0865 -4.250 -0.1487 0.00929 0.00406 -0.1028 0.9632 0.0968 -3.750 -0.0810 0.00887 0.00381 -0.1058 0.9627 0.1271 -3.500 -0.0447 0.00861 0.00366 -0.1078 0.9623 0.1495 -3.250 -0.0062 0.00832 0.00349 -0.1102 0.9618 0.1725 -3.000 0.0337 0.00800 0.00329 -0.1130 0.9613 0.2045 -2.750 0.0791 0.00752 0.00298 -0.1170 0.9605 0.2447 -2.500 0.1116 0.00701 0.00268 -0.1181 0.9537 0.2985 -2.250 0.1640 0.00602 0.00212 -0.1241 0.9487 0.4233 -2.000 0.2073 0.00529 0.00177 -0.1280 0.9416 0.5348 -1.750 0.2446 0.00504 0.00175 -0.1298 0.9314 0.6074 -1.500 0.2775 0.00502 0.00175 -0.1305 0.9143 0.6263 -1.250 0.2927 0.00641 0.00181 -0.1272 0.6066 0.6359 -1.000 0.3103 0.00749 0.00213 -0.1250 0.4102 0.6423 -0.750 0.3356 0.00795 0.00229 -0.1244 0.3336 0.6470 -0.500 0.3625 0.00831 0.00241 -0.1241 0.2798 0.6520 -0.250 0.3886 0.00869 0.00259 -0.1236 0.2290 0.6557 0.000 0.4142 0.00906 0.00284 -0.1229 0.1899 0.6592 0.250 0.4404 0.00941 0.00306 -0.1222 0.1604 0.6631 0.500 0.4676 0.00970 0.00323 -0.1219 0.1337 0.6661 0.750 0.4955 0.00994 0.00334 -0.1218 0.1117 0.6676 1.000 0.5237 0.01013 0.00345 -0.1217 0.0975 0.6685 1.250 0.5517 0.01033 0.00357 -0.1216 0.0844 0.6694 1.500 0.5795 0.01050 0.00367 -0.1214 0.0721 0.6705 1.750 0.6073 0.01067 0.00379 -0.1212 0.0632 0.6712 2.000 0.6351 0.01086 0.00391 -0.1211 0.0560 0.6717 2.250 0.6629 0.01103 0.00405 -0.1209 0.0505 0.6722 2.500 0.6909 0.01119 0.00418 -0.1208 0.0467 0.6726 2.750 0.7187 0.01138 0.00433 -0.1206 0.0433 0.6730 3.000 0.7466 0.01154 0.00448 -0.1204 0.0412 0.6734 3.250 0.7743 0.01172 0.00464 -0.1202 0.0389 0.6737 3.500 0.8019 0.01193 0.00482 -0.1200 0.0367 0.6741 3.750 0.8295 0.01210 0.00499 -0.1198 0.0351 0.6746 4.000 0.8569 0.01231 0.00518 -0.1195 0.0333 0.6751 4.250 0.8842 0.01254 0.00539 -0.1192 0.0317 0.6756 4.500 0.9116 0.01273 0.00559 -0.1190 0.0306 0.6760 4.750 0.9390 0.01294 0.00579 -0.1187 0.0294 0.6764 5.000 0.9660 0.01318 0.00602 -0.1184 0.0281 0.6768 5.250 0.9930 0.01344 0.00627 -0.1181 0.0271 0.6772 5.500 1.0200 0.01366 0.00651 -0.1177 0.0263 0.6776 5.750 1.0468 0.01391 0.00676 -0.1174 0.0254 0.6779 6.000 1.0735 0.01418 0.00702 -0.1170 0.0246 0.6783 6.250 1.0998 0.01448 0.00732 -0.1166 0.0237 0.6787 6.500 1.1261 0.01478 0.00763 -0.1161 0.0231 0.6791 6.750 1.1524 0.01506 0.00793 -0.1157 0.0226 0.6794 7.000 1.1785 0.01536 0.00825 -0.1152 0.0221 0.6798 7.250 1.2044 0.01568 0.00859 -0.1147 0.0216 0.6802 7.500 1.2301 0.01600 0.00892 -0.1141 0.0211 0.6806 7.750 1.2555 0.01635 0.00928 -0.1135 0.0206 0.6811 8.000 1.2806 0.01675 0.00969 -0.1129 0.0201 0.6816 8.250 1.3053 0.01717 0.01014 -0.1122 0.0197 0.6819 8.500 1.3302 0.01754 0.01055 -0.1115 0.0195 0.6822 8.750 1.3549 0.01793 0.01098 -0.1108 0.0192 0.6825 9.000 1.3792 0.01834 0.01142 -0.1100 0.0190 0.6828 9.250 1.4033 0.01876 0.01189 -0.1092 0.0187 0.6831 9.500 1.4271 0.01920 0.01237 -0.1083 0.0184 0.6834 9.750 1.4505 0.01965 0.01286 -0.1074 0.0182 0.6837 10.000 1.4736 0.02012 0.01337 -0.1065 0.0180 0.6840 10.250 1.4963 0.02062 0.01391 -0.1055 0.0178 0.6842 10.500 1.5186 0.02113 0.01447 -0.1044 0.0176 0.6845 10.750 1.5404 0.02168 0.01506 -0.1033 0.0174 0.6847 11.000 1.5615 0.02227 0.01570 -0.1020 0.0172 0.6849 11.250 1.5817 0.02292 0.01640 -0.1006 0.0170 0.6852 11.500 1.6007 0.02365 0.01720 -0.0991 0.0168 0.6854 11.750 1.6184 0.02448 0.01809 -0.0973 0.0166 0.6856 12.000 1.6372 0.02513 0.01882 -0.0957 0.0165 0.6859 12.250 1.6552 0.02582 0.01959 -0.0941 0.0164 0.6865 12.500 1.6724 0.02652 0.02039 -0.0923 0.0164 0.6870 12.750 1.6885 0.02727 0.02122 -0.0903 0.0163 0.6874 13.000 1.7032 0.02807 0.02211 -0.0881 0.0162 0.6877 13.250 1.7156 0.02890 0.02303 -0.0856 0.0161 0.6881 13.500 1.7232 0.02974 0.02397 -0.0822 0.0160 0.6884 13.750 1.7317 0.03067 0.02500 -0.0792 0.0160 0.6887 14.000 1.7395 0.03169 0.02611 -0.0761 0.0159 0.6890 14.250 1.7464 0.03277 0.02730 -0.0731 0.0158 0.6894 14.500 1.7519 0.03397 0.02860 -0.0700 0.0157 0.6897 14.750 1.7563 0.03528 0.03002 -0.0669 0.0157 0.6900 15.000 1.7600 0.03667 0.03151 -0.0640 0.0156 0.6903 15.250 1.7627 0.03818 0.03313 -0.0611 0.0155 0.6905 15.500 1.7636 0.03987 0.03494 -0.0583 0.0154 0.6908 15.750 1.7637 0.04173 0.03691 -0.0557 0.0153 0.6911 16.000 1.7612 0.04389 0.03919 -0.0533 0.0153 0.6914 16.250 1.7576 0.04631 0.04173 -0.0512 0.0152 0.6917 16.500 1.7508 0.04923 0.04479 -0.0495 0.0151 0.6919 16.750 1.7413 0.05270 0.04840 -0.0485 0.0151 0.6921 17.000 1.7279 0.05710 0.05296 -0.0485 0.0151 0.6924 17.250 1.7111 0.06266 0.05868 -0.0500 0.0150 0.6926 17.500 1.6866 0.07054 0.06676 -0.0541 0.0150 0.6927