XFOIL Version 6.96 Calculated polar for: GOE 290 (MVA 290) 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 ------ -------- --------- --------- -------- -------- -------- -13.750 -0.7326 0.06396 0.05909 -0.0709 1.0000 0.0428 -13.500 -0.7752 0.05417 0.04896 -0.0790 1.0000 0.0429 -13.250 -0.7982 0.04846 0.04299 -0.0831 1.0000 0.0431 -13.000 -0.8152 0.04453 0.03883 -0.0845 1.0000 0.0434 -12.750 -0.8304 0.04170 0.03580 -0.0835 1.0000 0.0437 -12.500 -0.8470 0.03972 0.03364 -0.0801 1.0000 0.0440 -12.250 -0.8601 0.03804 0.03177 -0.0760 1.0000 0.0443 -12.000 -0.8673 0.03641 0.02993 -0.0724 1.0000 0.0447 -11.750 -0.8542 0.03488 0.02828 -0.0718 0.9967 0.0451 -11.500 -0.8260 0.03358 0.02693 -0.0736 0.9914 0.0455 -11.250 -0.7978 0.03234 0.02563 -0.0752 0.9847 0.0461 -11.000 -0.7702 0.03113 0.02433 -0.0765 0.9770 0.0467 -10.750 -0.7418 0.02991 0.02298 -0.0779 0.9688 0.0474 -10.500 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0.0724 -5.750 -0.2513 0.01779 0.00832 -0.0704 0.6040 0.0748 -5.500 -0.2249 0.01751 0.00794 -0.0702 0.5955 0.0775 -5.250 -0.1988 0.01720 0.00756 -0.0699 0.5884 0.0803 -5.000 -0.1723 0.01688 0.00721 -0.0698 0.5813 0.0836 -4.750 -0.1454 0.01666 0.00690 -0.0696 0.5750 0.0872 -4.500 -0.1188 0.01639 0.00659 -0.0695 0.5699 0.0911 -4.250 -0.0914 0.01614 0.00633 -0.0694 0.5649 0.0958 -4.000 -0.0640 0.01591 0.00609 -0.0694 0.5601 0.1014 -3.750 -0.0365 0.01571 0.00586 -0.0694 0.5556 0.1090 -3.500 -0.0092 0.01551 0.00566 -0.0693 0.5515 0.1206 -3.250 0.0184 0.01525 0.00546 -0.0693 0.5474 0.1410 -3.000 0.0454 0.01487 0.00524 -0.0694 0.5433 0.1779 -2.750 0.0718 0.01445 0.00520 -0.0694 0.5396 0.2662 -2.500 0.0999 0.01440 0.00518 -0.0694 0.5362 0.3037 -2.250 0.1282 0.01440 0.00517 -0.0694 0.5330 0.3267 -2.000 0.1566 0.01442 0.00516 -0.0695 0.5295 0.3449 -1.750 0.1852 0.01440 0.00516 -0.0696 0.5254 0.3617 -1.500 0.2135 0.01437 0.00517 -0.0696 0.5211 0.3772 -1.250 0.2417 0.01436 0.00516 -0.0696 0.5170 0.3914 -1.000 0.2701 0.01439 0.00514 -0.0697 0.5132 0.4045 -0.750 0.2984 0.01440 0.00515 -0.0697 0.5099 0.4176 -0.500 0.3266 0.01436 0.00518 -0.0698 0.5064 0.4323 -0.250 0.3548 0.01433 0.00521 -0.0698 0.5028 0.4488 0.000 0.3829 0.01430 0.00524 -0.0698 0.4993 0.4663 0.250 0.4108 0.01427 0.00526 -0.0698 0.4958 0.4864 0.500 0.4384 0.01426 0.00529 -0.0697 0.4923 0.5102 0.750 0.4659 0.01419 0.00536 -0.0696 0.4887 0.5397 1.000 0.4931 0.01411 0.00544 -0.0694 0.4850 0.5771 1.250 0.5195 0.01399 0.00554 -0.0691 0.4813 0.6301 1.500 0.5445 0.01384 0.00564 -0.0683 0.4776 0.6998 1.750 0.5687 0.01373 0.00575 -0.0671 0.4742 0.7795 2.000 0.5955 0.01373 0.00589 -0.0664 0.4709 0.8557 2.250 0.6293 0.01376 0.00603 -0.0672 0.4667 0.9151 2.500 0.6674 0.01383 0.00612 -0.0693 0.4615 0.9549 2.750 0.7062 0.01394 0.00618 -0.0715 0.4570 0.9821 3.000 0.7464 0.01409 0.00625 -0.0742 0.4535 1.0000 3.250 0.7710 0.01420 0.00638 -0.0736 0.4497 1.0000 3.500 0.7958 0.01432 0.00651 -0.0731 0.4456 1.0000 3.750 0.8209 0.01445 0.00663 -0.0726 0.4416 1.0000 4.000 0.8461 0.01458 0.00670 -0.0722 0.4374 1.0000 4.250 0.8713 0.01472 0.00683 -0.0717 0.4324 1.0000 4.500 0.8964 0.01484 0.00698 -0.0713 0.4261 1.0000 4.750 0.9214 0.01496 0.00706 -0.0708 0.4200 1.0000 5.000 0.9465 0.01511 0.00722 -0.0703 0.4138 1.0000 5.250 0.9715 0.01526 0.00738 -0.0699 0.4068 1.0000 5.500 0.9959 0.01542 0.00750 -0.0693 0.3997 1.0000 5.750 1.0204 0.01558 0.00769 -0.0688 0.3899 1.0000 6.000 1.0440 0.01577 0.00785 -0.0682 0.3793 1.0000 6.250 1.0667 0.01600 0.00803 -0.0674 0.3670 1.0000 6.500 1.0890 0.01626 0.00826 -0.0665 0.3533 1.0000 6.750 1.1106 0.01657 0.00852 -0.0656 0.3393 1.0000 7.000 1.1306 0.01696 0.00883 -0.0645 0.3235 1.0000 7.250 1.1489 0.01742 0.00921 -0.0631 0.3069 1.0000 7.500 1.1661 0.01794 0.00965 -0.0616 0.2919 1.0000 7.750 1.1832 0.01847 0.01013 -0.0601 0.2800 1.0000 8.000 1.1992 0.01903 0.01065 -0.0584 0.2705 1.0000 8.250 1.2139 0.01962 0.01121 -0.0566 0.2619 1.0000 8.500 1.2261 0.02022 0.01180 -0.0544 0.2550 1.0000 8.750 1.2388 0.02087 0.01244 -0.0523 0.2479 1.0000 9.000 1.2490 0.02168 0.01322 -0.0501 0.2415 1.0000 9.250 1.2632 0.02235 0.01394 -0.0485 0.2361 1.0000 9.500 1.2756 0.02316 0.01476 -0.0469 0.2306 1.0000 9.750 1.2858 0.02412 0.01573 -0.0451 0.2257 1.0000 10.000 1.2979 0.02503 0.01669 -0.0437 0.2215 1.0000 10.250 1.3109 0.02595 0.01766 -0.0425 0.2170 1.0000 10.500 1.3204 0.02713 0.01888 -0.0411 0.2116 1.0000 10.750 1.3271 0.02859 0.02034 -0.0397 0.2069 1.0000 11.000 1.3400 0.02968 0.02153 -0.0389 0.2026 1.0000 11.250 1.3498 0.03106 0.02298 -0.0381 0.1973 1.0000 11.500 1.3554 0.03283 0.02479 -0.0371 0.1921 1.0000 11.750 1.3653 0.03432 0.02636 -0.0365 0.1859 1.0000 12.000 1.3696 0.03636 0.02844 -0.0359 0.1760 1.0000 12.250 1.3690 0.03896 0.03103 -0.0353 0.1491 1.0000 12.500 1.3481 0.04372 0.03559 -0.0348 0.1228 1.0000 12.750 1.3362 0.04769 0.03950 -0.0344 0.1122 1.0000 13.000 1.3298 0.05117 0.04301 -0.0341 0.1057 1.0000 13.250 1.3258 0.05446 0.04635 -0.0340 0.1005 1.0000 13.500 1.3223 0.05774 0.04969 -0.0340 0.0961 1.0000 13.750 1.3221 0.06072 0.05275 -0.0340 0.0906 1.0000 14.000 1.3194 0.06404 0.05614 -0.0342 0.0821 1.0000 14.250 1.3059 0.06871 0.06077 -0.0345 0.0588 1.0000 14.500 1.2879 0.07408 0.06609 -0.0352 0.0484 1.0000 14.750 1.2770 0.07870 0.07074 -0.0358 0.0448 1.0000 15.000 1.2689 0.08303 0.07514 -0.0364 0.0430 1.0000 15.250 1.2621 0.08727 0.07946 -0.0372 0.0416 1.0000 15.500 1.2559 0.09151 0.08378 -0.0380 0.0406 1.0000 15.750 1.2507 0.09567 0.08804 -0.0388 0.0398 1.0000 16.000 1.2454 0.09987 0.09234 -0.0398 0.0391 1.0000 16.250 1.2396 0.10422 0.09678 -0.0408 0.0385 1.0000 16.500 1.2333 0.10869 0.10135 -0.0420 0.0379 1.0000 16.750 1.2271 0.11321 0.10597 -0.0433 0.0374 1.0000 17.000 1.2207 0.11779 0.11064 -0.0447 0.0369 1.0000