XFOIL Version 6.96 Calculated polar for: 74-130 WP2 MOD 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 ------ -------- --------- --------- -------- -------- -------- -10.250 -0.1822 0.08555 0.08278 -0.0969 0.7742 0.0045 -8.250 -0.2347 0.05032 0.04754 -0.1138 0.7613 0.0051 -6.500 -0.1982 0.02229 0.01797 -0.1049 0.7493 0.0046 -6.250 -0.1837 0.01861 0.01384 -0.1033 0.7479 0.0045 -6.000 -0.1631 0.01636 0.01124 -0.1024 0.7466 0.0045 -5.750 -0.1401 0.01468 0.00928 -0.1017 0.7453 0.0045 -5.500 -0.1154 0.01359 0.00801 -0.1014 0.7439 0.0046 -5.250 -0.0901 0.01271 0.00699 -0.1012 0.7425 0.0046 -5.000 -0.0645 0.01200 0.00616 -0.1010 0.7411 0.0047 -4.750 -0.0385 0.01144 0.00551 -0.1008 0.7395 0.0048 -4.500 -0.0147 0.01044 0.00438 -0.1003 0.7380 0.0052 -4.250 0.0116 0.01004 0.00391 -0.1003 0.7365 0.0056 -4.000 0.0386 0.00975 0.00361 -0.1004 0.7350 0.0060 -3.750 0.0657 0.00946 0.00331 -0.1005 0.7334 0.0064 -3.500 0.0930 0.00919 0.00300 -0.1006 0.7316 0.0067 -3.250 0.1204 0.00894 0.00272 -0.1008 0.7297 0.0070 -3.000 0.1480 0.00873 0.00248 -0.1010 0.7277 0.0073 -2.750 0.1757 0.00857 0.00229 -0.1012 0.7257 0.0078 -2.500 0.2033 0.00836 0.00203 -0.1013 0.7237 0.0086 -2.250 0.2312 0.00819 0.00184 -0.1015 0.7215 0.0099 -2.000 0.2593 0.00804 0.00170 -0.1018 0.7189 0.0136 -1.750 0.2871 0.00784 0.00159 -0.1020 0.7162 0.0357 -1.500 0.3147 0.00762 0.00148 -0.1023 0.7134 0.0782 -1.250 0.3409 0.00701 0.00137 -0.1027 0.7107 0.2471 -1.000 0.3666 0.00607 0.00124 -0.1033 0.7078 0.5196 -0.750 0.3926 0.00543 0.00132 -0.1034 0.7043 0.7494 -0.500 0.4208 0.00549 0.00140 -0.1035 0.7004 0.7804 -0.250 0.4491 0.00555 0.00143 -0.1037 0.6965 0.7935 0.000 0.4776 0.00561 0.00147 -0.1039 0.6920 0.8013 0.250 0.5060 0.00565 0.00148 -0.1042 0.6863 0.8069 0.500 0.5338 0.00570 0.00152 -0.1043 0.6805 0.8117 0.750 0.5620 0.00575 0.00154 -0.1046 0.6734 0.8159 1.000 0.5903 0.00580 0.00155 -0.1049 0.6666 0.8186 1.250 0.6183 0.00584 0.00156 -0.1051 0.6588 0.8202 1.500 0.6461 0.00589 0.00158 -0.1053 0.6513 0.8214 1.750 0.6736 0.00595 0.00161 -0.1055 0.6434 0.8223 2.000 0.7014 0.00601 0.00166 -0.1057 0.6361 0.8231 2.500 0.7565 0.00617 0.00177 -0.1061 0.6219 0.8249 3.000 0.8113 0.00635 0.00193 -0.1065 0.6080 0.8266 3.250 0.8381 0.00646 0.00202 -0.1065 0.6002 0.8274 3.500 0.8645 0.00659 0.00212 -0.1066 0.5891 0.8282 3.750 0.8901 0.00677 0.00226 -0.1064 0.5747 0.8292 4.000 0.9151 0.00696 0.00240 -0.1061 0.5589 0.8302 4.250 0.9401 0.00716 0.00255 -0.1059 0.5405 0.8310 4.500 0.9648 0.00737 0.00270 -0.1056 0.5225 0.8318 4.750 0.9885 0.00762 0.00290 -0.1051 0.5010 0.8325 5.000 1.0059 0.00818 0.00321 -0.1035 0.4422 0.8334 5.250 1.0111 0.00933 0.00387 -0.0998 0.3442 0.8347 5.500 1.0229 0.01011 0.00438 -0.0973 0.2861 0.8358 5.750 1.0354 0.01080 0.00486 -0.0949 0.2394 0.8370 6.000 1.0474 0.01146 0.00533 -0.0924 0.1984 0.8384 6.250 1.0540 0.01211 0.00583 -0.0888 0.1589 0.8400 6.500 1.0594 0.01284 0.00639 -0.0852 0.1222 0.8415 6.750 1.0699 0.01344 0.00691 -0.0825 0.1012 0.8429 7.000 1.0751 0.01429 0.00761 -0.0792 0.0702 0.8445 7.250 1.0816 0.01518 0.00837 -0.0763 0.0457 0.8459 7.750 1.1059 0.01658 0.00970 -0.0725 0.0250 0.8486 8.000 1.1207 0.01719 0.01034 -0.0710 0.0205 0.8500 8.250 1.1348 0.01786 0.01102 -0.0696 0.0173 0.8515 8.500 1.1498 0.01850 0.01169 -0.0682 0.0145 0.8532 8.750 1.1640 0.01921 0.01241 -0.0668 0.0116 0.8550 9.000 1.1775 0.01998 0.01319 -0.0654 0.0088 0.8568 9.250 1.1901 0.02083 0.01404 -0.0639 0.0062 0.8585 9.500 1.2031 0.02167 0.01491 -0.0625 0.0046 0.8602 9.750 1.2156 0.02256 0.01584 -0.0611 0.0037 0.8619 10.000 1.2287 0.02341 0.01677 -0.0598 0.0033 0.8640 10.250 1.2413 0.02431 0.01773 -0.0584 0.0030 0.8663 10.500 1.2542 0.02522 0.01870 -0.0572 0.0028 0.8688 10.750 1.2662 0.02620 0.01975 -0.0559 0.0027 0.8714 11.000 1.2781 0.02721 0.02081 -0.0546 0.0024 0.8742 11.250 1.2883 0.02835 0.02203 -0.0532 0.0022 0.8777 11.500 1.2966 0.02967 0.02345 -0.0516 0.0020 0.8820 11.750 1.3046 0.03102 0.02490 -0.0501 0.0019 0.8870 12.000 1.3143 0.03225 0.02623 -0.0488 0.0019 0.8936 12.500 1.3307 0.03474 0.02899 -0.0457 0.0019 0.9291 13.000 1.3505 0.03763 0.03210 -0.0442 0.0018 1.0000 13.250 1.3577 0.03936 0.03392 -0.0431 0.0018 1.0000 13.500 1.3660 0.04102 0.03567 -0.0423 0.0018 1.0000 13.750 1.3721 0.04294 0.03768 -0.0414 0.0017 1.0000 14.000 1.3800 0.04471 0.03954 -0.0407 0.0017 1.0000 14.250 1.3862 0.04672 0.04164 -0.0400 0.0017 1.0000 14.500 1.3913 0.04890 0.04393 -0.0393 0.0016 1.0000 14.750 1.3963 0.05113 0.04625 -0.0388 0.0016 1.0000 15.000 1.4001 0.05357 0.04880 -0.0383 0.0015 1.0000 15.250 1.4037 0.05608 0.05142 -0.0380 0.0015 1.0000 15.500 1.4066 0.05876 0.05423 -0.0377 0.0015 1.0000 15.750 1.4084 0.06162 0.05721 -0.0376 0.0015 1.0000 16.000 1.4091 0.06470 0.06041 -0.0376 0.0014 1.0000 16.250 1.4098 0.06787 0.06369 -0.0377 0.0014 1.0000 16.500 1.4098 0.07122 0.06715 -0.0381 0.0014 1.0000 16.750 1.4068 0.07507 0.07114 -0.0385 0.0014 1.0000 17.000 1.4058 0.07870 0.07490 -0.0392 0.0013 1.0000 17.250 1.4012 0.08299 0.07932 -0.0401 0.0013 1.0000 17.500 1.3972 0.08731 0.08377 -0.0412 0.0013 1.0000 17.750 1.3897 0.09229 0.08890 -0.0426 0.0013 1.0000 18.000 1.3829 0.09730 0.09403 -0.0443 0.0012 1.0000 18.250 1.3734 0.10291 0.09980 -0.0464 0.0012 1.0000 18.500 1.3661 0.10831 0.10532 -0.0486 0.0012 1.0000 18.750 1.3535 0.11486 0.11203 -0.0515 0.0012 1.0000 19.000 1.3426 0.12128 0.11860 -0.0547 0.0012 1.0000 19.250 1.3299 0.12828 0.12574 -0.0584 0.0012 1.0000