XFOIL Version 6.96 Calculated polar for: MH 83 13.29% 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.2621 0.09790 0.09512 -0.0083 0.6214 0.0142 -8.750 -0.2554 0.09487 0.09206 -0.0098 0.6116 0.0146 -8.500 -0.2503 0.09144 0.08862 -0.0116 0.6032 0.0149 -8.250 -0.2585 0.08458 0.08176 -0.0159 0.5984 0.0159 -8.000 -0.2593 0.07981 0.07699 -0.0186 0.5916 0.0160 -7.750 -0.2595 0.07564 0.07282 -0.0208 0.5841 0.0160 -7.500 -0.2679 0.07119 0.06839 -0.0226 0.5775 0.0162 -7.250 -0.2658 0.06876 0.06596 -0.0238 0.5694 0.0163 -7.000 -0.3376 0.02286 0.01841 -0.0642 0.5867 0.0135 -6.750 -0.3128 0.02071 0.01592 -0.0648 0.5764 0.0135 -6.500 -0.2867 0.01905 0.01399 -0.0651 0.5660 0.0135 -6.250 -0.2598 0.01770 0.01241 -0.0652 0.5565 0.0136 -6.000 -0.2324 0.01657 0.01108 -0.0653 0.5465 0.0136 -5.750 -0.2046 0.01561 0.00995 -0.0653 0.5369 0.0137 -5.250 -0.1482 0.01412 0.00818 -0.0653 0.5169 0.0140 -5.000 -0.1197 0.01350 0.00743 -0.0653 0.5076 0.0141 -4.750 -0.0910 0.01302 0.00686 -0.0652 0.4986 0.0144 -4.500 -0.0623 0.01261 0.00635 -0.0652 0.4897 0.0148 -4.250 -0.0334 0.01216 0.00581 -0.0651 0.4806 0.0151 -4.000 -0.0045 0.01173 0.00528 -0.0650 0.4716 0.0154 -3.750 0.0246 0.01137 0.00484 -0.0650 0.4624 0.0157 -3.500 0.0538 0.01113 0.00452 -0.0649 0.4543 0.0160 -3.250 0.0827 0.01054 0.00386 -0.0650 0.4461 0.0166 -3.000 0.1119 0.01028 0.00355 -0.0650 0.4382 0.0171 -2.750 0.1412 0.01008 0.00330 -0.0649 0.4305 0.0177 -2.500 0.1705 0.00992 0.00307 -0.0649 0.4225 0.0184 -2.250 0.1999 0.00977 0.00287 -0.0649 0.4149 0.0190 -2.000 0.2292 0.00957 0.00260 -0.0649 0.4066 0.0201 -1.750 0.2586 0.00943 0.00244 -0.0649 0.4001 0.0217 -1.500 0.2879 0.00932 0.00229 -0.0649 0.3928 0.0241 -1.250 0.3174 0.00920 0.00215 -0.0649 0.3866 0.0290 -1.000 0.3466 0.00890 0.00202 -0.0650 0.3801 0.0746 -0.750 0.3758 0.00880 0.00198 -0.0651 0.3731 0.1093 -0.500 0.4050 0.00868 0.00195 -0.0652 0.3674 0.1421 -0.250 0.4341 0.00858 0.00194 -0.0653 0.3609 0.1893 0.000 0.4633 0.00849 0.00196 -0.0654 0.3552 0.2386 0.250 0.4924 0.00839 0.00198 -0.0655 0.3501 0.2907 0.500 0.5214 0.00830 0.00202 -0.0656 0.3445 0.3545 0.750 0.5502 0.00817 0.00209 -0.0657 0.3395 0.4351 1.250 0.6077 0.00791 0.00222 -0.0658 0.3301 0.6096 1.500 0.6355 0.00780 0.00233 -0.0657 0.3246 0.7133 1.750 0.6580 0.00736 0.00240 -0.0641 0.3217 0.8919 2.000 0.6907 0.00733 0.00242 -0.0648 0.3176 1.0000 2.250 0.7197 0.00746 0.00248 -0.0648 0.3135 1.0000 2.500 0.7484 0.00763 0.00258 -0.0649 0.3088 1.0000 2.750 0.7776 0.00771 0.00264 -0.0649 0.3063 1.0000 3.000 0.8065 0.00782 0.00271 -0.0650 0.3029 1.0000 3.250 0.8353 0.00796 0.00279 -0.0650 0.2993 1.0000 3.500 0.8639 0.00813 0.00291 -0.0650 0.2955 1.0000 3.750 0.8925 0.00828 0.00303 -0.0651 0.2924 1.0000 4.000 0.9214 0.00838 0.00312 -0.0651 0.2902 1.0000 4.250 0.9500 0.00850 0.00322 -0.0652 0.2874 1.0000 4.500 0.9785 0.00865 0.00334 -0.0652 0.2843 1.0000 4.750 1.0068 0.00883 0.00348 -0.0653 0.2810 1.0000 5.000 1.0348 0.00905 0.00366 -0.0653 0.2776 1.0000 5.250 1.0633 0.00916 0.00377 -0.0653 0.2760 1.0000 5.500 1.0917 0.00928 0.00390 -0.0654 0.2739 1.0000 5.750 1.1200 0.00942 0.00403 -0.0654 0.2713 1.0000 6.000 1.1480 0.00960 0.00418 -0.0654 0.2687 1.0000 6.250 1.1757 0.00980 0.00437 -0.0655 0.2659 1.0000 6.500 1.2029 0.01008 0.00461 -0.0654 0.2625 1.0000 6.750 1.2310 0.01020 0.00475 -0.0655 0.2612 1.0000 7.000 1.2590 0.01033 0.00491 -0.0655 0.2592 1.0000 7.250 1.2868 0.01049 0.00507 -0.0655 0.2570 1.0000 7.500 1.3142 0.01067 0.00526 -0.0655 0.2548 1.0000 7.750 1.3413 0.01089 0.00547 -0.0655 0.2524 1.0000 8.000 1.3678 0.01117 0.00574 -0.0655 0.2493 1.0000 8.250 1.3947 0.01140 0.00598 -0.0654 0.2470 1.0000 8.500 1.4221 0.01155 0.00617 -0.0655 0.2454 1.0000 8.750 1.4492 0.01173 0.00637 -0.0654 0.2436 1.0000 9.000 1.4760 0.01192 0.00659 -0.0654 0.2413 1.0000 9.250 1.5024 0.01215 0.00683 -0.0654 0.2388 1.0000 9.500 1.5281 0.01245 0.00711 -0.0653 0.2361 1.0000 9.750 1.5530 0.01281 0.00748 -0.0651 0.2330 1.0000 10.000 1.5797 0.01297 0.00769 -0.0650 0.2315 1.0000 10.250 1.6059 0.01316 0.00793 -0.0650 0.2295 1.0000 10.500 1.6316 0.01339 0.00819 -0.0649 0.2271 1.0000 10.750 1.6567 0.01366 0.00848 -0.0647 0.2244 1.0000 11.000 1.6806 0.01402 0.00884 -0.0644 0.2214 1.0000 11.250 1.7042 0.01439 0.00923 -0.0641 0.2185 1.0000 11.500 1.7295 0.01459 0.00949 -0.0640 0.2165 1.0000 11.750 1.7540 0.01484 0.00980 -0.0637 0.2140 1.0000 12.000 1.7773 0.01517 0.01014 -0.0634 0.2111 1.0000 12.250 1.7991 0.01559 0.01057 -0.0629 0.2078 1.0000 12.500 1.8204 0.01601 0.01102 -0.0624 0.2043 1.0000 12.750 1.8436 0.01627 0.01135 -0.0621 0.2013 1.0000 13.000 1.8643 0.01667 0.01177 -0.0615 0.1972 1.0000 13.250 1.8813 0.01726 0.01236 -0.0605 0.1930 1.0000 13.500 1.9002 0.01769 0.01285 -0.0596 0.1901 1.0000 13.750 1.9166 0.01815 0.01336 -0.0585 0.1864 1.0000 14.000 1.9245 0.01884 0.01408 -0.0563 0.1827 1.0000 14.250 1.9290 0.01983 0.01509 -0.0541 0.1781 1.0000 14.500 1.9391 0.02068 0.01599 -0.0528 0.1734 1.0000 14.750 1.9434 0.02203 0.01736 -0.0514 0.1686 1.0000 15.000 1.9484 0.02347 0.01884 -0.0503 0.1645 1.0000 15.250 1.9542 0.02498 0.02040 -0.0495 0.1596 1.0000 15.500 1.9539 0.02710 0.02255 -0.0487 0.1552 1.0000 15.750 1.9556 0.02917 0.02467 -0.0482 0.1505 1.0000 16.000 1.9545 0.03160 0.02716 -0.0478 0.1460 1.0000 16.250 1.9457 0.03490 0.03048 -0.0476 0.1408 1.0000 16.500 1.9423 0.03782 0.03348 -0.0476 0.1363 1.0000 16.750 1.9298 0.04176 0.03747 -0.0479 0.1318 1.0000 17.000 1.9175 0.04585 0.04163 -0.0484 0.1278 1.0000 17.250 1.9051 0.05006 0.04591 -0.0490 0.1238 1.0000 17.500 1.8841 0.05555 0.05146 -0.0503 0.1196 1.0000 17.750 1.8672 0.06077 0.05677 -0.0516 0.1161 1.0000 18.000 1.8489 0.06633 0.06242 -0.0532 0.1123 1.0000 18.250 1.8238 0.07303 0.06918 -0.0554 0.1085 1.0000 18.500 1.8039 0.07921 0.07546 -0.0576 0.1056 1.0000 18.750 1.7841 0.08557 0.08190 -0.0599 0.1020 1.0000 19.000 1.7595 0.09276 0.08917 -0.0627 0.0987 1.0000