XFOIL Version 6.96 Calculated polar for: GOE 142 (MVA H.19) 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -7.000 -0.3613 0.08730 0.08400 -0.0279 1.0000 0.0311 -6.750 -0.3567 0.08313 0.07986 -0.0247 1.0000 0.0318 -6.500 -0.3487 0.07989 0.07665 -0.0243 1.0000 0.0325 -6.250 -0.3403 0.07688 0.07366 -0.0251 1.0000 0.0333 -6.000 -0.3319 0.07395 0.07074 -0.0263 1.0000 0.0342 -5.750 -0.3231 0.07103 0.06784 -0.0277 1.0000 0.0352 -5.500 -0.3139 0.06813 0.06495 -0.0292 1.0000 0.0364 -5.250 -0.3033 0.06520 0.06201 -0.0308 1.0000 0.0379 -5.000 -0.2859 0.06224 0.05899 -0.0342 1.0000 0.0401 -4.750 -0.2526 0.05995 0.05645 -0.0407 1.0000 0.0417 -4.500 -0.2347 0.05713 0.05349 -0.0419 1.0000 0.0418 -4.250 -0.2322 0.05116 0.04762 -0.0417 1.0000 0.0431 -4.000 -0.2231 0.04867 0.04515 -0.0406 1.0000 0.0443 -3.750 -0.1849 0.04544 0.04184 -0.0453 0.9962 0.0494 -3.500 -0.1235 0.04039 0.03623 -0.0543 0.9919 0.0556 -3.250 -0.0896 0.03670 0.03255 -0.0580 0.9874 0.0580 -3.000 -0.0447 0.03371 0.02936 -0.0627 0.9838 0.0639 -2.250 0.1262 0.00636 0.00058 -0.0771 0.9561 0.0533 -1.750 0.1804 0.01686 0.00999 -0.0786 0.9597 0.0558 -1.500 0.2239 0.01526 0.00824 -0.0816 0.9553 0.0604 -1.250 0.2608 0.01459 0.00734 -0.0828 0.9458 0.0679 -1.000 0.2962 0.01334 0.00609 -0.0840 0.9366 0.0756 -0.750 0.3307 0.01258 0.00530 -0.0848 0.9268 0.0866 -0.500 0.3609 0.01201 0.00471 -0.0846 0.9138 0.0981 -0.250 0.3882 0.01147 0.00423 -0.0840 0.8986 0.1142 0.000 0.4143 0.01103 0.00386 -0.0831 0.8813 0.1356 0.250 0.4402 0.01056 0.00352 -0.0822 0.8631 0.1770 0.500 0.4635 0.00838 0.00327 -0.0806 0.8456 1.0000 0.750 0.4891 0.00840 0.00308 -0.0795 0.8246 1.0000 1.000 0.5148 0.00846 0.00295 -0.0785 0.8026 1.0000 1.250 0.5405 0.00854 0.00286 -0.0776 0.7787 1.0000 1.500 0.5663 0.00865 0.00280 -0.0768 0.7544 1.0000 1.750 0.5920 0.00879 0.00277 -0.0759 0.7289 1.0000 2.000 0.6178 0.00896 0.00277 -0.0752 0.7021 1.0000 2.250 0.6436 0.00915 0.00281 -0.0745 0.6744 1.0000 2.500 0.6694 0.00937 0.00287 -0.0738 0.6465 1.0000 2.750 0.6951 0.00961 0.00297 -0.0732 0.6182 1.0000 3.000 0.7208 0.00988 0.00308 -0.0726 0.5902 1.0000 3.250 0.7465 0.01016 0.00322 -0.0721 0.5625 1.0000 3.500 0.7721 0.01045 0.00338 -0.0716 0.5356 1.0000 3.750 0.7977 0.01077 0.00360 -0.0711 0.5098 1.0000 4.000 0.8233 0.01110 0.00382 -0.0706 0.4852 1.0000 4.250 0.8487 0.01145 0.00406 -0.0701 0.4614 1.0000 4.500 0.8743 0.01179 0.00433 -0.0697 0.4386 1.0000 4.750 0.8995 0.01218 0.00464 -0.0693 0.4176 1.0000 5.000 0.9251 0.01254 0.00497 -0.0689 0.3964 1.0000 5.250 0.9503 0.01294 0.00531 -0.0684 0.3774 1.0000 5.500 0.9754 0.01336 0.00568 -0.0680 0.3592 1.0000 5.750 1.0006 0.01376 0.00610 -0.0676 0.3413 1.0000 6.000 1.0256 0.01419 0.00653 -0.0671 0.3246 1.0000 6.250 1.0504 0.01464 0.00697 -0.0667 0.3085 1.0000 6.500 1.0749 0.01509 0.00741 -0.0662 0.2924 1.0000 6.750 1.0990 0.01548 0.00781 -0.0657 0.2734 1.0000 7.000 1.1231 0.01583 0.00822 -0.0652 0.2529 1.0000 7.250 1.1467 0.01628 0.00867 -0.0646 0.2354 1.0000 7.500 1.1706 0.01669 0.00915 -0.0641 0.2170 1.0000 7.750 1.1941 0.01713 0.00963 -0.0636 0.1963 1.0000 8.000 1.2172 0.01761 0.01016 -0.0630 0.1707 1.0000 8.250 1.2380 0.01842 0.01084 -0.0622 0.1271 1.0000 8.500 1.2492 0.02075 0.01260 -0.0603 0.0589 1.0000 8.750 1.2638 0.02246 0.01431 -0.0585 0.0449 1.0000 9.000 1.2764 0.02427 0.01621 -0.0565 0.0390 1.0000 9.250 1.2915 0.02568 0.01772 -0.0548 0.0345 1.0000 9.500 1.2978 0.02820 0.02026 -0.0522 0.0309 1.0000 9.750 1.3130 0.02965 0.02188 -0.0505 0.0293 1.0000 10.000 1.3263 0.03144 0.02387 -0.0486 0.0277 1.0000 10.250 1.3391 0.03342 0.02599 -0.0467 0.0263 1.0000 10.500 1.3513 0.03552 0.02824 -0.0449 0.0251 1.0000 10.750 1.3616 0.03772 0.03054 -0.0431 0.0238 1.0000 11.000 1.3688 0.04194 0.03496 -0.0414 0.0224 1.0000 11.250 1.3712 0.04510 0.03844 -0.0389 0.0218 1.0000 11.500 1.3707 0.04761 0.04123 -0.0361 0.0216 1.0000 11.750 1.3666 0.05045 0.04436 -0.0334 0.0214 1.0000 12.000 1.3590 0.05364 0.04783 -0.0310 0.0213 1.0000 12.250 1.3485 0.05723 0.05169 -0.0293 0.0212 1.0000 12.500 1.3355 0.06124 0.05598 -0.0283 0.0212 1.0000 12.750 1.3204 0.06575 0.06074 -0.0281 0.0213 1.0000 13.000 1.3036 0.07080 0.06603 -0.0289 0.0213 1.0000 13.250 1.2855 0.07646 0.07191 -0.0307 0.0214 1.0000 13.500 1.2662 0.08273 0.07839 -0.0334 0.0215 1.0000 13.750 1.2458 0.08967 0.08552 -0.0369 0.0216 1.0000 14.000 1.2245 0.09726 0.09328 -0.0410 0.0218 1.0000