XFOIL Version 6.94 Calculated polar for: MH 70 11.08% 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3017 0.00661 0.00234 -0.0497 0.6578 0.9565 0.500 0.3848 0.00673 0.00218 -0.0550 0.6306 0.9907 1.000 0.4521 0.00673 0.00209 -0.0573 0.6127 1.0000 1.500 0.5017 0.00694 0.00206 -0.0559 0.5835 1.0000 2.000 0.5535 0.00706 0.00212 -0.0550 0.5628 1.0000 2.500 0.6042 0.00735 0.00220 -0.0538 0.5288 1.0000 3.000 0.6567 0.00758 0.00233 -0.0530 0.5027 1.0000 3.500 0.7088 0.00791 0.00253 -0.0522 0.4709 1.0000 4.000 0.7600 0.00836 0.00279 -0.0513 0.4320 1.0000 4.500 0.8127 0.00873 0.00307 -0.0507 0.4034 1.0000 5.000 0.8644 0.00921 0.00343 -0.0500 0.3681 1.0000 5.500 0.9152 0.00978 0.00388 -0.0492 0.3326 1.0000 6.000 0.9651 0.01045 0.00438 -0.0484 0.2974 1.0000 6.500 1.0159 0.01102 0.00491 -0.0477 0.2706 1.0000 7.000 1.0654 0.01170 0.00557 -0.0468 0.2426 1.0000 7.500 1.1122 0.01261 0.00632 -0.0457 0.2122 1.0000 8.000 1.1616 0.01323 0.00697 -0.0449 0.1943 1.0000 8.500 1.2063 0.01422 0.00789 -0.0435 0.1713 1.0000 9.000 1.2525 0.01501 0.00867 -0.0423 0.1548 1.0000 9.500 1.2942 0.01609 0.00976 -0.0406 0.1364 1.0000 10.000 1.3361 0.01705 0.01075 -0.0389 0.1230 1.0000 10.500 1.3704 0.01841 0.01211 -0.0363 0.1063 1.0000 11.000 1.4036 0.01952 0.01340 -0.0335 0.0947 1.0000 11.500 1.4200 0.02152 0.01542 -0.0290 0.0803 1.0000 12.000 1.4483 0.02298 0.01703 -0.0265 0.0726 1.0000 12.500 1.4567 0.02601 0.02003 -0.0230 0.0598 1.0000 13.000 1.4784 0.02830 0.02250 -0.0211 0.0540 1.0000 13.500 1.4862 0.03192 0.02619 -0.0191 0.0463 1.0000 14.000 1.4709 0.03814 0.03258 -0.0172 0.0381 1.0000 14.500 1.4857 0.04168 0.03634 -0.0166 0.0363 1.0000 15.000 1.4898 0.04659 0.04144 -0.0167 0.0325 1.0000 15.500 1.4744 0.05425 0.04931 -0.0176 0.0297 1.0000 16.000 1.4459 0.06445 0.05970 -0.0203 0.0255 1.0000 16.500 1.4079 0.07633 0.07194 -0.0241 0.0233 1.0000 17.000 1.3925 0.08578 0.08171 -0.0277 0.0223 1.0000 17.500 1.3825 0.09510 0.09126 -0.0320 0.0217 1.0000 18.000 1.3626 0.10625 0.10269 -0.0374 0.0212 1.0000 18.500 1.3466 0.11707 0.11374 -0.0432 0.0201 1.0000 19.000 1.3278 0.12830 0.12521 -0.0494 0.0192 1.0000 19.500 1.3077 0.14018 0.13729 -0.0567 0.0179 1.0000 20.000 1.2829 0.15246 0.14978 -0.0649 0.0170 1.0000 20.500 1.2582 0.16602 0.16352 -0.0737 0.0159 1.0000 21.000 1.2369 0.18000 0.17764 -0.0823 0.0147 1.0000 21.500 1.1837 0.20498 0.20292 -0.0961 0.0147 1.0000 22.000 1.0314 0.28305 0.28097 -0.1233 0.0144 1.0000 22.500 1.0413 0.29030 0.28826 -0.1266 0.0129 1.0000 23.500 1.0254 0.32263 0.32063 -0.1355 0.0103 1.0000 24.000 1.0075 0.33807 0.33610 -0.1382 0.0093 1.0000 24.500 0.8937 0.32448 0.32271 -0.1299 0.0070 1.0000 26.000 0.8469 0.33149 0.32984 -0.1319 0.0109 1.0000 26.500 0.8453 0.33742 0.33578 -0.1348 0.0077 1.0000 27.500 0.8348 0.34193 0.34036 -0.1377 0.0106 1.0000 28.000 0.8318 0.34555 0.34400 -0.1395 0.0104 1.0000 28.500 0.8336 0.35032 0.34881 -0.1423 0.0064 1.0000 29.000 0.8319 0.35378 0.35232 -0.1444 0.0067 1.0000 29.500 0.8330 0.35369 0.35228 -0.1457 0.0040 1.0000 30.000 0.8310 0.35871 0.35732 -0.1483 0.0045 1.0000