XFOIL Version 6.96 Calculated polar for: RAF 30 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.500 -0.9961 0.13862 0.13560 0.0024 1.0000 0.0121 -19.250 -1.0190 0.12974 0.12659 -0.0024 1.0000 0.0123 -19.000 -1.0428 0.12102 0.11774 -0.0071 1.0000 0.0122 -18.750 -1.0637 0.11307 0.10967 -0.0113 1.0000 0.0123 -18.500 -1.0840 0.10545 0.10193 -0.0152 1.0000 0.0124 -18.250 -1.1028 0.09826 0.09461 -0.0189 1.0000 0.0125 -18.000 -1.1212 0.09132 0.08754 -0.0224 1.0000 0.0125 -17.750 -1.1360 0.08513 0.08123 -0.0256 1.0000 0.0126 -17.500 -1.1493 0.07924 0.07521 -0.0285 1.0000 0.0128 -17.250 -1.1625 0.07355 0.06940 -0.0313 1.0000 0.0129 -17.000 -1.1724 0.06853 0.06425 -0.0337 1.0000 0.0131 -16.750 -1.1816 0.06375 0.05935 -0.0359 1.0000 0.0133 -16.500 -1.1880 0.05955 0.05502 -0.0377 1.0000 0.0136 -16.250 -1.1962 0.05529 0.05063 -0.0393 1.0000 0.0137 -16.000 -1.1998 0.05176 0.04697 -0.0406 1.0000 0.0139 -15.750 -1.2034 0.04836 0.04345 -0.0416 1.0000 0.0141 -15.500 -1.2054 0.04525 0.04025 -0.0424 1.0000 0.0145 -15.250 -1.2041 0.04262 0.03755 -0.0430 1.0000 0.0148 -15.000 -1.2031 0.04007 0.03490 -0.0433 1.0000 0.0150 -14.750 -1.1985 0.03798 0.03273 -0.0434 1.0000 0.0154 -14.500 -1.1906 0.03632 0.03100 -0.0434 1.0000 0.0160 -14.250 -1.1861 0.03439 0.02897 -0.0430 1.0000 0.0163 -14.000 -1.1785 0.03284 0.02733 -0.0426 1.0000 0.0168 -13.750 -1.1712 0.03134 0.02572 -0.0419 1.0000 0.0173 -13.500 -1.1635 0.02993 0.02421 -0.0411 1.0000 0.0178 -13.250 -1.1575 0.02849 0.02269 -0.0399 1.0000 0.0181 -13.000 -1.1500 0.02725 0.02140 -0.0387 1.0000 0.0186 -12.750 -1.1399 0.02627 0.02036 -0.0374 1.0000 0.0191 -12.500 -1.1288 0.02542 0.01945 -0.0360 1.0000 0.0196 -12.250 -1.1181 0.02458 0.01855 -0.0343 1.0000 0.0202 -12.000 -1.1068 0.02385 0.01775 -0.0326 1.0000 0.0209 -11.750 -1.0955 0.02315 0.01698 -0.0306 1.0000 0.0215 -11.500 -1.0836 0.02254 0.01629 -0.0286 1.0000 0.0220 -11.250 -1.0715 0.02199 0.01565 -0.0264 1.0000 0.0224 -11.000 -1.0666 0.02117 0.01479 -0.0230 1.0000 0.0229 -10.750 -1.0588 0.02054 0.01413 -0.0199 1.0000 0.0235 -10.500 -1.0461 0.02000 0.01356 -0.0176 1.0000 0.0242 -10.250 -1.0315 0.01950 0.01302 -0.0155 1.0000 0.0249 -10.000 -1.0164 0.01902 0.01250 -0.0135 1.0000 0.0256 -9.750 -1.0008 0.01854 0.01197 -0.0115 1.0000 0.0263 -9.500 -0.9843 0.01812 0.01148 -0.0097 1.0000 0.0271 -9.250 -0.9677 0.01769 0.01100 -0.0078 1.0000 0.0275 -9.000 -0.9512 0.01725 0.01051 -0.0059 1.0000 0.0280 -8.750 -0.9381 0.01658 0.00982 -0.0034 1.0000 0.0290 -8.500 -0.9225 0.01608 0.00930 -0.0013 1.0000 0.0298 -8.250 -0.9059 0.01565 0.00884 0.0006 1.0000 0.0307 -8.000 -0.8888 0.01526 0.00842 0.0025 1.0000 0.0314 -7.750 -0.8651 0.01485 0.00798 0.0030 0.9989 0.0323 -7.500 -0.8324 0.01444 0.00752 0.0017 0.9955 0.0334 -7.250 -0.8011 0.01405 0.00708 0.0006 0.9912 0.0342 -7.000 -0.7701 0.01360 0.00660 -0.0003 0.9862 0.0354 -6.750 -0.7403 0.01316 0.00616 -0.0010 0.9802 0.0371 -6.250 -0.6800 0.01243 0.00540 -0.0024 0.9656 0.0413 -6.000 -0.6462 0.01205 0.00502 -0.0039 0.9591 0.0458 -5.750 -0.6137 0.01162 0.00465 -0.0051 0.9499 0.0566 -5.500 -0.5790 0.01109 0.00427 -0.0069 0.9404 0.0859 -5.000 -0.5063 0.01030 0.00363 -0.0110 0.9165 0.1275 -4.750 -0.4745 0.00991 0.00333 -0.0121 0.9006 0.1546 -4.500 -0.4471 0.00953 0.00306 -0.0122 0.8837 0.1897 -4.250 -0.4224 0.00919 0.00283 -0.0117 0.8672 0.2317 -4.000 -0.3976 0.00897 0.00266 -0.0111 0.8517 0.2602 -3.750 -0.3728 0.00878 0.00251 -0.0105 0.8370 0.2836 -3.500 -0.3484 0.00859 0.00236 -0.0098 0.8232 0.3107 -3.000 -0.3003 0.00820 0.00209 -0.0082 0.7969 0.3690 -2.750 -0.2763 0.00802 0.00198 -0.0074 0.7842 0.3994 -2.500 -0.2524 0.00785 0.00189 -0.0065 0.7706 0.4327 -2.250 -0.2290 0.00769 0.00180 -0.0055 0.7543 0.4688 -2.000 -0.2050 0.00760 0.00174 -0.0046 0.7364 0.4986 -1.750 -0.1808 0.00750 0.00169 -0.0038 0.7205 0.5274 -1.500 -0.1560 0.00741 0.00165 -0.0030 0.7077 0.5536 -1.250 -0.1306 0.00736 0.00162 -0.0024 0.6952 0.5746 -1.000 -0.1048 0.00733 0.00159 -0.0019 0.6833 0.5896 -0.750 -0.0788 0.00732 0.00156 -0.0014 0.6718 0.6019 -0.500 -0.0525 0.00731 0.00155 -0.0009 0.6597 0.6135 0.000 0.0000 0.00730 0.00153 0.0000 0.6370 0.6369 0.500 0.0525 0.00731 0.00155 0.0009 0.6134 0.6600 0.750 0.0788 0.00732 0.00156 0.0014 0.6017 0.6718 1.000 0.1048 0.00733 0.00159 0.0019 0.5895 0.6833 1.250 0.1306 0.00736 0.00162 0.0024 0.5747 0.6953 1.500 0.1561 0.00741 0.00165 0.0030 0.5540 0.7077 1.750 0.1808 0.00750 0.00169 0.0038 0.5272 0.7207 2.000 0.2049 0.00760 0.00174 0.0047 0.4981 0.7366 2.250 0.2286 0.00771 0.00180 0.0056 0.4656 0.7543 2.500 0.2524 0.00785 0.00189 0.0065 0.4328 0.7705 2.750 0.2762 0.00803 0.00198 0.0074 0.3987 0.7840 3.000 0.3003 0.00820 0.00209 0.0082 0.3693 0.7969 3.250 0.3244 0.00839 0.00222 0.0090 0.3403 0.8098 3.500 0.3484 0.00860 0.00236 0.0098 0.3102 0.8230 3.750 0.3728 0.00878 0.00251 0.0105 0.2833 0.8370 4.000 0.3975 0.00897 0.00266 0.0111 0.2596 0.8517 4.250 0.4223 0.00920 0.00283 0.0117 0.2307 0.8671 4.500 0.4471 0.00954 0.00306 0.0122 0.1891 0.8837 4.750 0.4744 0.00991 0.00333 0.0121 0.1547 0.9005 5.000 0.5063 0.01030 0.00363 0.0110 0.1273 0.9165 5.500 0.5789 0.01109 0.00427 0.0070 0.0857 0.9404 5.750 0.6136 0.01161 0.00465 0.0051 0.0567 0.9498 6.000 0.6462 0.01206 0.00503 0.0039 0.0454 0.9591 6.250 0.6801 0.01243 0.00540 0.0024 0.0413 0.9656 6.750 0.7402 0.01317 0.00616 0.0011 0.0370 0.9802 7.000 0.7702 0.01359 0.00660 0.0003 0.0354 0.9862 7.250 0.8011 0.01405 0.00708 -0.0006 0.0342 0.9912 7.500 0.8324 0.01444 0.00752 -0.0017 0.0334 0.9955 7.750 0.8650 0.01486 0.00799 -0.0030 0.0323 0.9989 8.000 0.8889 0.01526 0.00842 -0.0026 0.0315 1.0000 8.250 0.9060 0.01565 0.00884 -0.0006 0.0307 1.0000 8.500 0.9226 0.01608 0.00929 0.0013 0.0299 1.0000 8.750 0.9381 0.01659 0.00982 0.0034 0.0290 1.0000 9.000 0.9515 0.01723 0.01050 0.0058 0.0281 1.0000 9.250 0.9678 0.01769 0.01100 0.0078 0.0276 1.0000 9.500 0.9848 0.01809 0.01145 0.0096 0.0270 1.0000 9.750 1.0011 0.01852 0.01194 0.0115 0.0263 1.0000 10.000 1.0167 0.01900 0.01248 0.0135 0.0256 1.0000 10.250 1.0314 0.01951 0.01304 0.0155 0.0249 1.0000 10.500 1.0465 0.01998 0.01353 0.0175 0.0241 1.0000 10.750 1.0589 0.02053 0.01412 0.0199 0.0236 1.0000 11.000 1.0667 0.02116 0.01479 0.0230 0.0230 1.0000 11.250 1.0720 0.02197 0.01563 0.0263 0.0224 1.0000 11.500 1.0835 0.02255 0.01629 0.0286 0.0220 1.0000 11.750 1.0952 0.02317 0.01700 0.0307 0.0215 1.0000 12.000 1.1063 0.02388 0.01779 0.0326 0.0209 1.0000 12.250 1.1173 0.02465 0.01863 0.0344 0.0203 1.0000 12.500 1.1289 0.02542 0.01946 0.0360 0.0197 1.0000 12.750 1.1399 0.02628 0.02038 0.0374 0.0191 1.0000 13.000 1.1494 0.02731 0.02146 0.0387 0.0186 1.0000 13.250 1.1583 0.02844 0.02264 0.0399 0.0181 1.0000 13.500 1.1640 0.02992 0.02419 0.0410 0.0178 1.0000 13.750 1.1720 0.03129 0.02568 0.0419 0.0174 1.0000 14.000 1.1789 0.03284 0.02733 0.0425 0.0169 1.0000 14.250 1.1863 0.03442 0.02900 0.0430 0.0164 1.0000 14.500 1.1927 0.03616 0.03084 0.0433 0.0158 1.0000 14.750 1.1982 0.03807 0.03283 0.0434 0.0155 1.0000 15.000 1.2040 0.04004 0.03487 0.0432 0.0150 1.0000 15.250 1.2069 0.04240 0.03732 0.0429 0.0147 1.0000 15.500 1.2082 0.04501 0.04000 0.0423 0.0144 1.0000 15.750 1.2051 0.04827 0.04335 0.0415 0.0141 1.0000 16.000 1.2020 0.05161 0.04682 0.0404 0.0139 1.0000 16.250 1.1973 0.05528 0.05062 0.0392 0.0137 1.0000 16.500 1.1919 0.05919 0.05465 0.0376 0.0134 1.0000 16.750 1.1844 0.06354 0.05913 0.0358 0.0132 1.0000 17.000 1.1759 0.06821 0.06393 0.0336 0.0131 1.0000 17.250 1.1628 0.07371 0.06956 0.0310 0.0129 1.0000 17.500 1.1526 0.07896 0.07493 0.0284 0.0127 1.0000 17.750 1.1376 0.08509 0.08119 0.0253 0.0127 1.0000 18.000 1.1214 0.09151 0.08774 0.0221 0.0127 1.0000 18.250 1.1046 0.09826 0.09461 0.0186 0.0125 1.0000 18.500 1.0858 0.10545 0.10193 0.0149 0.0124 1.0000 18.750 1.0667 0.11286 0.10945 0.0111 0.0123 1.0000 19.000 1.0443 0.12108 0.11780 0.0068 0.0123 1.0000