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 = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.250 -0.2137 0.08997 0.08793 -0.0723 -0.0007 4.4521 -12.000 -0.2075 0.08862 0.08658 -0.0714 -0.0009 4.4525 -11.750 -0.2032 0.08573 0.08369 -0.0721 -0.0011 4.4532 -11.500 -0.2040 0.08091 0.07888 -0.0744 -0.0013 4.4543 -11.250 -0.2129 0.07378 0.07177 -0.0788 -0.0014 4.4548 -11.000 -0.2001 0.07183 0.06981 -0.0795 -0.0014 4.4551 -10.750 -0.1960 0.06785 0.06583 -0.0822 -0.0015 4.4556 -10.500 -0.2632 0.05784 0.05577 -0.0889 -0.0016 4.4546 -10.250 -0.2761 0.05503 0.05293 -0.0903 -0.0014 4.4546 -10.000 -0.2851 0.05223 0.05008 -0.0922 -0.0012 4.4545 -9.750 -0.3032 0.04920 0.04695 -0.0944 -0.0011 4.4544 -9.500 -0.3199 0.04899 0.04676 -0.0919 -0.0005 4.4541 -8.750 -0.3480 0.04036 0.03771 -0.0912 0.0000 4.4552 -8.500 -0.3453 0.03673 0.03371 -0.0915 0.0000 4.4564 -8.250 -0.3278 0.03523 0.03220 -0.0921 0.0000 4.4568 -7.750 -0.3413 0.03232 0.02907 -0.0854 -0.0004 4.4573 -5.750 -0.2477 0.01847 0.01328 -0.0703 0.0051 4.4548 -5.500 -0.2219 0.01730 0.01201 -0.0696 0.0055 4.4517 -5.250 -0.1973 0.01639 0.01108 -0.0693 0.0059 4.4499 -5.000 -0.2011 0.01618 0.01081 -0.0652 0.0114 4.4486 -4.750 -0.1800 0.01564 0.01026 -0.0645 0.0129 4.4477 -4.500 -0.1578 0.01507 0.00969 -0.0640 0.0138 4.4469 -4.250 -0.1348 0.01462 0.00922 -0.0637 0.0146 4.4461 -4.000 -0.1112 0.01427 0.00885 -0.0634 0.0151 4.4454 -3.750 -0.1137 0.01413 0.00871 -0.0597 0.0228 4.4452 -3.500 -0.0913 0.01383 0.00838 -0.0592 0.0242 4.4451 -3.250 -0.0676 0.01360 0.00810 -0.0589 0.0252 4.4451 -3.000 -0.0432 0.01342 0.00788 -0.0587 0.0259 4.4456 -2.750 -0.0396 0.01335 0.00780 -0.0558 0.0331 4.4462 -2.500 -0.0184 0.01316 0.00757 -0.0551 0.0353 4.4476 -2.250 0.0044 0.01284 0.00737 -0.0547 0.0366 4.4501 -2.000 0.0211 0.01167 0.00722 -0.0544 0.0377 3.7023 -1.750 0.0279 0.01080 0.00723 -0.0523 0.0421 2.8315 -1.500 0.0646 0.01140 0.00815 -0.0521 0.0465 2.3290 -1.250 0.1095 0.01231 0.00903 -0.0529 0.0470 2.2033 -1.000 0.1686 0.01358 0.01026 -0.0547 0.0456 2.1413 -0.750 0.2004 0.01370 0.01034 -0.0549 0.0475 2.1288 -0.500 0.2282 0.01361 0.01021 -0.0549 0.0491 2.1167 -0.250 0.2562 0.01350 0.01006 -0.0550 0.0503 2.1027 0.000 0.2842 0.01343 0.00995 -0.0552 0.0512 2.0839 0.250 0.3126 0.01337 0.00986 -0.0554 0.0519 2.0676 0.500 0.3442 0.01316 0.00964 -0.0559 0.0524 2.0602 0.750 0.3754 0.01295 0.00941 -0.0563 0.0530 2.0509 1.000 0.4060 0.01272 0.00917 -0.0567 0.0535 2.0404 1.250 0.4110 0.01277 0.00924 -0.0538 0.0675 2.0285 1.500 0.4407 0.01248 0.00894 -0.0541 0.0686 2.0174 1.750 0.4584 0.01234 0.00882 -0.0529 0.0776 2.0071 2.000 0.4947 0.01184 0.00831 -0.0542 0.0738 2.0009 2.250 0.5245 0.01126 0.00772 -0.0550 0.0711 2.0009 2.500 0.5223 0.01120 0.00767 -0.0516 0.0890 2.0009 2.750 0.5450 0.01072 0.00719 -0.0515 0.0906 2.0009 3.000 0.5491 0.01056 0.00703 -0.0488 0.1070 2.0009 3.250 0.5703 0.01005 0.00652 -0.0484 0.1108 2.0009 3.500 0.5923 0.00954 0.00603 -0.0480 0.1132 2.0009 3.750 0.6144 0.00906 0.00555 -0.0477 0.1150 2.0009 4.000 0.6376 0.00858 0.00508 -0.0475 0.1166 2.0009 4.250 0.6617 0.00811 0.00463 -0.0474 0.1181 2.0009 4.500 0.6871 0.00765 0.00420 -0.0474 0.1194 2.0009 4.750 0.7134 0.00720 0.00377 -0.0476 0.1211 2.0009 5.500 0.7368 0.00678 0.00343 -0.0407 0.1732 2.0009 5.750 0.7450 0.00640 0.00306 -0.0382 0.2042 2.0009 6.000 0.7502 0.00609 0.00272 -0.0353 0.2527 2.0009 6.250 0.7764 0.00532 0.00170 -0.0348 0.3956 2.0009 6.500 0.7707 0.00539 0.00148 -0.0306 0.6070 2.0009 6.750 0.7542 0.00573 0.00162 -0.0253 0.7952 2.0009 7.000 0.7363 0.00617 0.00185 -0.0201 0.9918 2.0009 7.250 0.7143 0.00673 0.00219 -0.0146 1.2502 2.0009 7.500 0.6956 0.00731 0.00254 -0.0098 1.5208 2.0009 7.750 0.6782 0.00794 0.00290 -0.0053 1.8491 2.0009 8.000 0.6644 0.00853 0.00324 -0.0015 2.2238 2.0009 8.250 0.6490 0.00923 0.00362 0.0024 2.7129 2.0009 8.500 0.6259 0.01025 0.00420 0.0066 3.5737 2.0009 8.750 0.6173 0.01086 0.00467 0.0096 4.1987 2.0009 9.000 0.6217 0.01104 0.00491 0.0115 4.2167 2.0009 9.250 0.6258 0.01122 0.00516 0.0134 4.2245 2.0009 9.500 0.6295 0.01143 0.00544 0.0153 4.2301 2.0009 9.750 0.6324 0.01165 0.00574 0.0172 4.2325 2.0009 10.000 0.6357 0.01187 0.00603 0.0191 4.2337 2.0009 10.250 0.6380 0.01214 0.00637 0.0209 4.2346 2.0009 10.500 0.6402 0.01241 0.00672 0.0228 4.2346 2.0009 10.750 0.6410 0.01274 0.00713 0.0246 4.2352 2.0009 11.000 0.6414 0.01309 0.00755 0.0264 4.2346 2.0009 11.250 0.6405 0.01351 0.00804 0.0282 4.2339 2.0009 11.500 0.6384 0.01399 0.00859 0.0300 4.2333 2.0009 11.750 0.6352 0.01452 0.00919 0.0317 4.2324 2.0009 12.000 0.6304 0.01515 0.00988 0.0334 4.2317 2.0009 12.250 0.6294 0.01562 0.01042 0.0348 4.2305 2.0009 12.500 0.6297 0.01604 0.01090 0.0362 4.2283 2.0009 12.750 0.6287 0.01654 0.01148 0.0376 4.2252 2.0009 13.000 0.6265 0.01711 0.01212 0.0389 4.2214 2.0009 13.250 0.6237 0.01772 0.01280 0.0401 4.2182 2.0009 13.500 0.6207 0.01835 0.01349 0.0413 4.2145 2.0009 13.750 0.6179 0.01899 0.01417 0.0424 4.2109 2.0009 14.000 0.6170 0.01949 0.01467 0.0436 4.2067 2.0009 14.250 0.6206 0.01978 0.01497 0.0447 4.2030 2.0009