XFOIL Version 6.96 Calculated polar for: GOE 134 (MVA H.12) AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.2854 0.11536 0.11192 -0.0271 1.0000 0.0217 -10.250 -0.2869 0.11212 0.10870 -0.0286 1.0000 0.0217 -10.000 -0.2871 0.10866 0.10526 -0.0297 1.0000 0.0218 -9.750 -0.2865 0.10511 0.10171 -0.0307 1.0000 0.0218 -9.500 -0.2860 0.10148 0.09811 -0.0316 1.0000 0.0218 -9.250 -0.2858 0.09785 0.09450 -0.0325 1.0000 0.0218 -9.000 -0.2863 0.09418 0.09087 -0.0332 1.0000 0.0218 -8.750 -0.2790 0.09049 0.08720 -0.0317 1.0000 0.0221 -8.500 -0.2750 0.08734 0.08408 -0.0310 1.0000 0.0225 -8.250 -0.2747 0.08421 0.08099 -0.0307 1.0000 0.0228 -8.000 -0.2765 0.08115 0.07796 -0.0305 1.0000 0.0231 -7.750 -0.2796 0.07823 0.07509 -0.0300 1.0000 0.0236 -7.500 -0.2852 0.07549 0.07241 -0.0292 1.0000 0.0243 -7.250 -0.2950 0.07298 0.06996 -0.0280 1.0000 0.0250 -7.000 -0.3768 0.07813 0.07484 -0.0367 1.0000 0.0218 -6.750 -0.3759 0.07675 0.07354 -0.0317 1.0000 0.0225 -6.500 -0.3729 0.07448 0.07130 -0.0310 1.0000 0.0234 -6.250 -0.3349 0.06775 0.06438 -0.0440 0.9947 0.0269 -6.000 -0.3022 0.06131 0.05770 -0.0521 0.9891 0.0271 -5.750 -0.2705 0.05548 0.05161 -0.0580 0.9849 0.0271 -5.500 -0.2402 0.05010 0.04591 -0.0623 0.9792 0.0272 -5.250 -0.2200 0.04743 0.04345 -0.0644 0.9757 0.0288 -5.000 -0.1787 0.04411 0.03953 -0.0685 0.9690 0.0342 -4.750 -0.1460 0.03959 0.03464 -0.0717 0.9640 0.0344 -4.500 -0.1226 0.03554 0.03063 -0.0736 0.9560 0.0357 -4.250 -0.0836 0.03566 0.03022 -0.0755 0.9496 0.0434 -3.750 -0.0235 0.02748 0.02127 -0.0773 0.9298 0.0342 -3.500 0.0047 0.02476 0.01857 -0.0790 0.9191 0.0370 -3.250 0.0368 0.02242 0.01562 -0.0791 0.9056 0.0353 -3.000 0.0674 0.02102 0.01388 -0.0792 0.8898 0.0349 -2.750 0.0959 0.01953 0.01218 -0.0794 0.8701 0.0357 -2.500 0.1242 0.01854 0.01109 -0.0794 0.8472 0.0372 -2.250 0.1526 0.01753 0.00979 -0.0791 0.8213 0.0371 -2.000 0.1805 0.01668 0.00864 -0.0786 0.7956 0.0369 -1.750 0.2079 0.01599 0.00770 -0.0781 0.7724 0.0370 -1.500 0.2352 0.01543 0.00693 -0.0777 0.7522 0.0372 -1.250 0.2624 0.01497 0.00632 -0.0774 0.7343 0.0380 -1.000 0.2897 0.01461 0.00585 -0.0772 0.7182 0.0394 -0.750 0.3171 0.01424 0.00537 -0.0769 0.7030 0.0399 -0.500 0.3445 0.01390 0.00495 -0.0767 0.6884 0.0399 -0.250 0.3720 0.01361 0.00459 -0.0766 0.6739 0.0401 0.000 0.3996 0.01337 0.00429 -0.0765 0.6595 0.0404 0.250 0.4272 0.01317 0.00404 -0.0765 0.6447 0.0409 0.500 0.4549 0.01303 0.00383 -0.0764 0.6299 0.0415 0.750 0.4826 0.01295 0.00365 -0.0764 0.6143 0.0422 1.000 0.5103 0.01291 0.00352 -0.0763 0.5989 0.0433 1.250 0.5380 0.01285 0.00338 -0.0763 0.5833 0.0466 1.500 0.5656 0.01287 0.00331 -0.0762 0.5677 0.0486 1.750 0.5931 0.01292 0.00328 -0.0761 0.5523 0.0508 2.250 0.6412 0.01083 0.00336 -0.0746 0.5234 1.0000 2.500 0.6684 0.01102 0.00342 -0.0745 0.5093 1.0000 2.750 0.6956 0.01122 0.00350 -0.0744 0.4948 1.0000 3.000 0.7226 0.01143 0.00359 -0.0743 0.4803 1.0000 3.250 0.7496 0.01164 0.00372 -0.0742 0.4659 1.0000 3.750 0.8034 0.01208 0.00401 -0.0740 0.4392 1.0000 4.000 0.8303 0.01231 0.00420 -0.0739 0.4264 1.0000 4.250 0.8570 0.01256 0.00439 -0.0738 0.4137 1.0000 4.500 0.8835 0.01281 0.00460 -0.0737 0.4015 1.0000 4.750 0.9099 0.01309 0.00484 -0.0736 0.3903 1.0000 5.000 0.9364 0.01335 0.00509 -0.0735 0.3798 1.0000 5.250 0.9627 0.01363 0.00536 -0.0733 0.3694 1.0000 5.500 0.9887 0.01393 0.00565 -0.0731 0.3583 1.0000 5.750 1.0142 0.01426 0.00594 -0.0729 0.3467 1.0000 6.000 1.0400 0.01456 0.00625 -0.0727 0.3350 1.0000 6.250 1.0655 0.01488 0.00658 -0.0725 0.3230 1.0000 6.500 1.0908 0.01521 0.00693 -0.0722 0.3115 1.0000 6.750 1.1156 0.01557 0.00729 -0.0719 0.3001 1.0000 7.000 1.1404 0.01592 0.00766 -0.0716 0.2886 1.0000 7.250 1.1655 0.01625 0.00808 -0.0713 0.2785 1.0000 7.500 1.1899 0.01663 0.00849 -0.0709 0.2667 1.0000 7.750 1.2135 0.01703 0.00891 -0.0704 0.2509 1.0000 8.000 1.2366 0.01748 0.00935 -0.0699 0.2328 1.0000 8.250 1.2587 0.01800 0.00986 -0.0693 0.2135 1.0000 8.500 1.2799 0.01860 0.01041 -0.0685 0.1866 1.0000 8.750 1.2988 0.01942 0.01108 -0.0675 0.1520 1.0000 9.000 1.3157 0.02041 0.01192 -0.0662 0.1233 1.0000 9.250 1.3319 0.02145 0.01288 -0.0648 0.1021 1.0000 9.500 1.3485 0.02239 0.01380 -0.0634 0.0831 1.0000 9.750 1.3616 0.02358 0.01488 -0.0616 0.0607 1.0000 10.000 1.3717 0.02493 0.01612 -0.0594 0.0362 1.0000 10.250 1.3759 0.02660 0.01765 -0.0564 0.0214 1.0000 10.500 1.3826 0.02786 0.01899 -0.0535 0.0188 1.0000 10.750 1.3866 0.02921 0.02048 -0.0504 0.0172 1.0000 11.000 1.3893 0.03077 0.02220 -0.0474 0.0160 1.0000 11.250 1.3940 0.03227 0.02386 -0.0450 0.0154 1.0000 11.500 1.3975 0.03396 0.02573 -0.0428 0.0148 1.0000 11.750 1.3994 0.03590 0.02783 -0.0408 0.0141 1.0000 12.000 1.3995 0.03812 0.03022 -0.0391 0.0135 1.0000 12.250 1.3979 0.04070 0.03296 -0.0378 0.0129 1.0000 12.500 1.3943 0.04370 0.03613 -0.0370 0.0124 1.0000 12.750 1.3886 0.04719 0.03979 -0.0367 0.0121 1.0000 13.000 1.3807 0.05116 0.04391 -0.0368 0.0118 1.0000 13.250 1.3708 0.05558 0.04848 -0.0372 0.0116 1.0000 13.500 1.3599 0.06024 0.05330 -0.0379 0.0114 1.0000 13.750 1.3520 0.06465 0.05784 -0.0387 0.0113 1.0000 14.000 1.3455 0.06894 0.06228 -0.0395 0.0112 1.0000 14.250 1.3386 0.07336 0.06684 -0.0405 0.0110 1.0000 14.500 1.3318 0.07786 0.07148 -0.0415 0.0109 1.0000 14.750 1.3250 0.08242 0.07618 -0.0427 0.0108 1.0000 15.000 1.3185 0.08698 0.08087 -0.0439 0.0106 1.0000