XFOIL Version 6.96 Calculated polar for: GOE 741 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 ------ -------- --------- --------- -------- -------- -------- -9.250 -0.6147 0.04291 0.03701 -0.0337 0.6019 0.0358 -9.000 -0.6275 0.03801 0.03149 -0.0311 0.5982 0.0359 -8.750 -0.6203 0.03549 0.02862 -0.0293 0.5940 0.0361 -8.500 -0.6054 0.03389 0.02683 -0.0280 0.5899 0.0364 -8.250 -0.5888 0.03240 0.02516 -0.0268 0.5853 0.0366 -8.000 -0.5709 0.03103 0.02359 -0.0257 0.5806 0.0369 -7.750 -0.5515 0.02987 0.02224 -0.0246 0.5763 0.0374 -7.500 -0.5316 0.02875 0.02090 -0.0235 0.5724 0.0379 -7.250 -0.5107 0.02760 0.01954 -0.0225 0.5682 0.0384 -7.000 -0.4892 0.02642 0.01814 -0.0215 0.5640 0.0390 -6.750 -0.4669 0.02530 0.01677 -0.0206 0.5603 0.0395 -6.500 -0.4438 0.02427 0.01548 -0.0197 0.5568 0.0400 -6.250 -0.4198 0.02338 0.01432 -0.0189 0.5536 0.0405 -6.000 -0.3950 0.02256 0.01339 -0.0183 0.5501 0.0409 -5.750 -0.3695 0.02190 0.01271 -0.0178 0.5462 0.0414 -5.500 -0.3439 0.02131 0.01206 -0.0173 0.5425 0.0420 -5.250 -0.3180 0.02076 0.01143 -0.0168 0.5392 0.0427 -5.000 -0.2920 0.02024 0.01081 -0.0163 0.5363 0.0435 -4.750 -0.2658 0.01977 0.01021 -0.0158 0.5336 0.0445 -4.500 -0.2390 0.01932 0.00967 -0.0154 0.5305 0.0457 -4.250 -0.2126 0.01886 0.00923 -0.0150 0.5270 0.0468 -4.000 -0.1860 0.01849 0.00885 -0.0146 0.5236 0.0480 -3.750 -0.1593 0.01812 0.00844 -0.0142 0.5206 0.0494 -3.500 -0.1326 0.01778 0.00801 -0.0138 0.5180 0.0509 -3.250 -0.1062 0.01745 0.00765 -0.0133 0.5155 0.0526 -3.000 -0.0794 0.01719 0.00737 -0.0129 0.5129 0.0547 -2.750 -0.0522 0.01693 0.00710 -0.0126 0.5098 0.0576 -2.500 -0.0253 0.01668 0.00691 -0.0123 0.5065 0.0614 -2.250 0.0018 0.01646 0.00671 -0.0119 0.5036 0.0664 -2.000 0.0290 0.01628 0.00654 -0.0116 0.5009 0.0731 -1.750 0.0561 0.01612 0.00639 -0.0113 0.4985 0.0816 -1.500 0.0833 0.01601 0.00624 -0.0110 0.4961 0.0919 -1.250 0.1104 0.01590 0.00614 -0.0107 0.4935 0.1030 -0.750 0.1643 0.01563 0.00600 -0.0101 0.4874 0.1265 -0.250 0.2178 0.01542 0.00601 -0.0095 0.4820 0.1678 0.000 0.2448 0.01537 0.00599 -0.0092 0.4794 0.1926 0.250 0.2716 0.01533 0.00596 -0.0088 0.4770 0.2143 0.500 0.2981 0.01530 0.00599 -0.0085 0.4743 0.2343 0.750 0.3245 0.01525 0.00603 -0.0082 0.4713 0.2528 1.000 0.3506 0.01520 0.00605 -0.0078 0.4681 0.2716 1.250 0.3766 0.01513 0.00605 -0.0073 0.4650 0.2942 1.500 0.4019 0.01499 0.00602 -0.0068 0.4622 0.3326 1.750 0.4157 0.01394 0.00593 -0.0041 0.4598 0.6300 2.250 0.5690 0.01423 0.00688 -0.0218 0.4481 0.9602 2.500 0.6138 0.01437 0.00694 -0.0250 0.4439 0.9714 2.750 0.6606 0.01450 0.00694 -0.0286 0.4405 0.9818 3.000 0.7126 0.01459 0.00703 -0.0335 0.4365 0.9903 3.250 0.7602 0.01462 0.00706 -0.0376 0.4322 0.9970 3.500 0.7969 0.01466 0.00707 -0.0395 0.4284 1.0000 3.750 0.8220 0.01474 0.00709 -0.0390 0.4251 1.0000 4.000 0.8470 0.01486 0.00714 -0.0385 0.4219 1.0000 4.250 0.8719 0.01501 0.00736 -0.0381 0.4176 1.0000 4.500 0.8967 0.01515 0.00751 -0.0376 0.4135 1.0000 4.750 0.9213 0.01528 0.00761 -0.0371 0.4099 1.0000 5.000 0.9458 0.01540 0.00768 -0.0365 0.4067 1.0000 5.250 0.9700 0.01559 0.00791 -0.0360 0.4026 1.0000 5.500 0.9939 0.01579 0.00815 -0.0355 0.3981 1.0000 5.750 1.0177 0.01596 0.00832 -0.0349 0.3940 1.0000 6.000 1.0413 0.01611 0.00843 -0.0342 0.3903 1.0000 6.250 1.0644 0.01635 0.00871 -0.0336 0.3857 1.0000 6.500 1.0871 0.01658 0.00899 -0.0329 0.3805 1.0000 6.750 1.1096 0.01678 0.00917 -0.0322 0.3759 1.0000 7.000 1.1317 0.01701 0.00941 -0.0314 0.3713 1.0000 7.250 1.1530 0.01731 0.00978 -0.0305 0.3658 1.0000 7.500 1.1740 0.01758 0.01004 -0.0296 0.3607 1.0000 7.750 1.1943 0.01786 0.01030 -0.0286 0.3559 1.0000 8.000 1.2136 0.01822 0.01073 -0.0275 0.3498 1.0000 8.250 1.2322 0.01855 0.01107 -0.0263 0.3442 1.0000 8.500 1.2497 0.01893 0.01146 -0.0250 0.3387 1.0000 8.750 1.2659 0.01936 0.01193 -0.0235 0.3326 1.0000 9.000 1.2808 0.01979 0.01235 -0.0218 0.3273 1.0000 9.250 1.2942 0.02029 0.01289 -0.0200 0.3219 1.0000 9.500 1.3053 0.02084 0.01347 -0.0179 0.3163 1.0000 9.750 1.3143 0.02142 0.01404 -0.0155 0.3115 1.0000 10.000 1.3207 0.02210 0.01476 -0.0129 0.3069 1.0000 10.250 1.3172 0.02291 0.01562 -0.0091 0.3025 1.0000 10.500 1.3137 0.02391 0.01662 -0.0058 0.2979 1.0000 10.750 1.3157 0.02492 0.01760 -0.0034 0.2940 1.0000 11.000 1.3179 0.02613 0.01889 -0.0015 0.2894 1.0000 11.250 1.3206 0.02741 0.02021 0.0002 0.2847 1.0000 11.500 1.3245 0.02868 0.02146 0.0017 0.2802 1.0000 11.750 1.3287 0.03004 0.02285 0.0030 0.2761 1.0000 12.000 1.3320 0.03157 0.02445 0.0041 0.2718 1.0000 12.250 1.3350 0.03314 0.02604 0.0051 0.2671 1.0000 12.750 1.3411 0.03645 0.02941 0.0069 0.2583 1.0000 13.000 1.3424 0.03837 0.03138 0.0076 0.2535 1.0000 13.250 1.3467 0.04000 0.03302 0.0083 0.2496 1.0000 13.500 1.3522 0.04152 0.03453 0.0090 0.2459 1.0000 13.750 1.3524 0.04372 0.03685 0.0094 0.2421 1.0000 14.000 1.3536 0.04584 0.03904 0.0098 0.2381 1.0000 14.250 1.3576 0.04769 0.04093 0.0102 0.2344 1.0000 14.500 1.3658 0.04910 0.04230 0.0106 0.2311 1.0000 14.750 1.3646 0.05170 0.04503 0.0106 0.2274 1.0000 15.000 1.3626 0.05442 0.04785 0.0106 0.2229 1.0000 15.250 1.3647 0.05666 0.05012 0.0106 0.2188 1.0000 15.500 1.3724 0.05818 0.05161 0.0109 0.2150 1.0000 15.750 1.3658 0.06166 0.05526 0.0104 0.2108 1.0000 16.000 1.3633 0.06463 0.05832 0.0101 0.2066 1.0000 16.250 1.3653 0.06701 0.06073 0.0100 0.2026 1.0000 16.500 1.3687 0.06922 0.06296 0.0098 0.1989 1.0000 16.750 1.3579 0.07345 0.06735 0.0090 0.1939 1.0000 17.000 1.3542 0.07670 0.07065 0.0084 0.1887 1.0000 17.250 1.3518 0.07981 0.07381 0.0079 0.1838 1.0000 17.500 1.3400 0.08436 0.07849 0.0068 0.1782 1.0000 17.750 1.3376 0.08756 0.08171 0.0061 0.1731 1.0000 18.000 1.3240 0.09247 0.08673 0.0048 0.1670 1.0000 18.250 1.3166 0.09650 0.09080 0.0037 0.1614 1.0000