XFOIL Version 6.96 Calculated polar for: UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN 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 ------ -------- --------- --------- -------- -------- -------- -13.500 -0.1672 0.08592 0.08413 -0.0793 0.0000 4.4082 -13.250 -0.1613 0.08177 0.07998 -0.0811 0.0000 4.4085 -13.000 -0.1595 0.07631 0.07453 -0.0834 0.0000 4.4086 -12.750 -0.1549 0.07239 0.07061 -0.0853 0.0000 4.4090 -12.500 -0.1553 0.06717 0.06540 -0.0879 -0.0001 4.4092 -12.250 -0.1563 0.06227 0.06051 -0.0905 -0.0001 4.4095 -12.000 -0.1638 0.05616 0.05441 -0.0941 -0.0002 4.4098 -11.750 -0.2264 0.03757 0.03567 -0.1068 -0.0002 4.4095 -11.500 -0.2555 0.03268 0.03062 -0.1110 -0.0003 4.4095 -11.250 -0.2777 0.02951 0.02730 -0.1129 -0.0004 4.4095 -11.000 -0.3003 0.02674 0.02436 -0.1135 -0.0004 4.4095 -10.750 -0.3194 0.02493 0.02240 -0.1128 -0.0004 4.4096 -10.500 -0.3236 0.02316 0.02046 -0.1123 -0.0005 4.4099 -10.250 -0.3222 0.02140 0.01854 -0.1117 -0.0004 4.4103 -10.000 -0.3171 0.01958 0.01652 -0.1109 -0.0004 4.4107 -9.750 -0.3081 0.01796 0.01471 -0.1102 -0.0004 4.4113 -9.500 -0.2963 0.01648 0.01302 -0.1094 -0.0003 4.4119 -9.250 -0.2823 0.01510 0.01145 -0.1087 -0.0002 4.4122 -9.000 -0.2665 0.01391 0.01009 -0.1080 -0.0001 4.4126 -8.750 -0.2492 0.01284 0.00886 -0.1074 0.0000 4.4128 -8.500 -0.2308 0.01188 0.00775 -0.1068 0.0001 4.4130 -8.250 -0.2116 0.01106 0.00680 -0.1062 0.0002 4.4133 -8.000 -0.1917 0.01032 0.00594 -0.1057 0.0004 4.4135 -7.750 -0.1713 0.00979 0.00530 -0.1051 0.0005 4.4140 -7.500 -0.1511 0.00938 0.00473 -0.1045 0.0006 4.4152 -7.250 -0.1303 0.00822 0.00356 -0.1042 0.0008 4.4165 -7.000 -0.1094 0.00767 0.00299 -0.1037 0.0009 4.4177 -6.750 -0.0884 0.00721 0.00250 -0.1033 0.0011 4.4185 -6.500 -0.0675 0.00678 0.00203 -0.1027 0.0014 4.4187 -6.250 -0.0468 0.00635 0.00157 -0.1022 0.0018 4.4180 -6.000 -0.0262 0.00598 0.00118 -0.1016 0.0021 4.4174 -5.750 -0.0056 0.00566 0.00083 -0.1010 0.0025 4.4169 -5.500 0.0151 0.00537 0.00052 -0.1005 0.0030 4.4166 -5.250 0.0360 0.00510 0.00024 -0.0999 0.0034 4.4163 4.500 0.7436 0.00308 0.00007 -0.0556 0.2826 2.0479 4.750 0.7286 0.00341 0.00020 -0.0496 0.4163 2.0420 5.000 0.7138 0.00382 0.00046 -0.0439 0.5662 2.0360 5.250 0.6968 0.00432 0.00079 -0.0380 0.7428 2.0298 5.500 0.6872 0.00476 0.00109 -0.0334 0.9019 2.0241 5.750 0.6821 0.00515 0.00135 -0.0294 1.0774 2.0190 6.000 0.6775 0.00556 0.00161 -0.0257 1.2692 2.0144 6.250 0.6666 0.00611 0.00190 -0.0214 1.5913 2.0103 6.500 0.6526 0.00677 0.00221 -0.0169 2.0557 2.0067 6.750 0.6434 0.00739 0.00251 -0.0131 2.5472 2.0036 7.000 0.6193 0.00848 0.00306 -0.0079 3.7126 2.0009 7.250 0.6173 0.00882 0.00332 -0.0051 4.3110 2.0009 7.500 0.6241 0.00889 0.00342 -0.0032 4.3200 2.0009 7.750 0.6300 0.00899 0.00355 -0.0012 4.3246 2.0009 8.000 0.6360 0.00909 0.00369 0.0008 4.3270 2.0009 8.250 0.6417 0.00919 0.00384 0.0027 4.3292 2.0009 8.500 0.6465 0.00933 0.00402 0.0047 4.3306 2.0009 8.750 0.6514 0.00947 0.00421 0.0067 4.3315 2.0009 9.000 0.6550 0.00965 0.00444 0.0088 4.3323 2.0009 9.250 0.6590 0.00982 0.00466 0.0108 4.3325 2.0009 9.500 0.6622 0.01002 0.00491 0.0128 4.3327 2.0009 9.750 0.6649 0.01023 0.00517 0.0148 4.3328 2.0009 10.000 0.6674 0.01045 0.00544 0.0167 4.3329 2.0009 10.250 0.6687 0.01071 0.00575 0.0187 4.3330 2.0009 10.500 0.6704 0.01097 0.00606 0.0207 4.3330 2.0009 10.750 0.6701 0.01129 0.00645 0.0227 4.3331 2.0009 11.000 0.6702 0.01162 0.00683 0.0246 4.3330 2.0009 11.250 0.6693 0.01198 0.00725 0.0265 4.3329 2.0009 11.500 0.6676 0.01239 0.00772 0.0283 4.3328 2.0009 11.750 0.6655 0.01281 0.00820 0.0301 4.3327 2.0009 12.000 0.6619 0.01332 0.00878 0.0319 4.3326 2.0009 12.250 0.6580 0.01385 0.00938 0.0336 4.3325 2.0009 12.500 0.6534 0.01443 0.01002 0.0352 4.3323 2.0009 12.750 0.6497 0.01498 0.01063 0.0367 4.3321 2.0009 13.000 0.6476 0.01549 0.01119 0.0381 4.3319 2.0009 13.250 0.6452 0.01602 0.01178 0.0394 4.3318 2.0009 13.500 0.6437 0.01651 0.01232 0.0406 4.3316 2.0009 13.750 0.6419 0.01703 0.01290 0.0418 4.3313 2.0009 14.000 0.6404 0.01754 0.01347 0.0429 4.3309 2.0009 14.250 0.6392 0.01806 0.01404 0.0439 4.3308 2.0009 14.500 0.6380 0.01859 0.01462 0.0448 4.3303 2.0009 14.750 0.6374 0.01910 0.01519 0.0458 4.3297 2.0009 15.000 0.6367 0.01961 0.01576 0.0466 4.3292 2.0009 15.250 0.6370 0.02009 0.01630 0.0475 4.3281 2.0009 15.500 0.6373 0.02058 0.01684 0.0484 4.3267 2.0009 15.750 0.6399 0.02091 0.01724 0.0494 4.3236 2.0009 16.000 0.6444 0.02116 0.01754 0.0504 4.3207 2.0009 16.250 0.6499 0.02139 0.01782 0.0514 4.3181 2.0009 16.500 0.6551 0.02169 0.01816 0.0524 4.3163 2.0009 16.750 0.6621 0.02195 0.01847 0.0533 4.3139 2.0009 17.250 0.6830 0.02252 0.01920 0.0557 4.2925 2.0009 17.500 0.6764 0.02338 0.02017 0.0559 4.2958 2.0009 17.750 0.6714 0.02418 0.02102 0.0561 4.3009 2.0009 18.000 0.6562 0.02557 0.02252 0.0557 4.3141 2.0009 18.250 0.6548 0.02649 0.02353 0.0560 4.3125 2.0009 18.500 0.6434 0.02781 0.02498 0.0556 4.3147 2.0009 18.750 0.6339 0.02909 0.02637 0.0552 4.3167 2.0009 19.000 0.6266 0.03045 0.02782 0.0550 4.3157 2.0009 19.250 0.6161 0.03198 0.02947 0.0542 4.3179 2.0009