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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.500 -0.7891 0.06500 0.06195 -0.0330 0.6745 0.0264 -13.250 -0.7377 0.07048 0.06749 -0.0280 0.6612 0.0266 -13.000 -0.9049 0.04136 0.03765 -0.0496 0.6680 0.0261 -12.750 -0.9325 0.03815 0.03423 -0.0456 0.6620 0.0261 -12.500 -0.9548 0.03552 0.03138 -0.0405 0.6549 0.0262 -12.250 -0.9688 0.03240 0.02798 -0.0366 0.6480 0.0264 -12.000 -0.9654 0.03043 0.02582 -0.0341 0.6401 0.0265 -11.750 -0.9557 0.02891 0.02414 -0.0320 0.6309 0.0266 -11.500 -0.9417 0.02771 0.02284 -0.0303 0.6224 0.0268 -11.250 -0.9248 0.02680 0.02182 -0.0288 0.6132 0.0270 -11.000 -0.9064 0.02599 0.02092 -0.0275 0.6051 0.0272 -10.750 -0.8878 0.02513 0.01995 -0.0261 0.5968 0.0273 -10.500 -0.8679 0.02439 0.01909 -0.0249 0.5892 0.0275 -10.250 -0.8482 0.02351 0.01810 -0.0237 0.5823 0.0277 -10.000 -0.8277 0.02271 0.01716 -0.0225 0.5752 0.0279 -9.750 -0.8066 0.02190 0.01624 -0.0214 0.5691 0.0281 -9.500 -0.7849 0.02112 0.01534 -0.0203 0.5637 0.0283 -9.250 -0.7626 0.02038 0.01449 -0.0193 0.5584 0.0284 -9.000 -0.7398 0.01970 0.01368 -0.0183 0.5527 0.0287 -8.750 -0.7164 0.01902 0.01291 -0.0174 0.5493 0.0288 -8.500 -0.6924 0.01841 0.01221 -0.0166 0.5452 0.0291 -8.250 -0.6679 0.01786 0.01156 -0.0158 0.5409 0.0293 -8.000 -0.6431 0.01737 0.01096 -0.0151 0.5362 0.0295 -7.750 -0.6178 0.01692 0.01043 -0.0144 0.5324 0.0297 -7.500 -0.5919 0.01652 0.00996 -0.0138 0.5297 0.0298 -7.250 -0.5672 0.01581 0.00918 -0.0130 0.5267 0.0301 -7.000 -0.5433 0.01500 0.00831 -0.0122 0.5235 0.0305 -6.750 -0.5176 0.01454 0.00780 -0.0116 0.5200 0.0308 -6.500 -0.4915 0.01420 0.00741 -0.0111 0.5159 0.0312 -6.250 -0.4648 0.01387 0.00706 -0.0106 0.5132 0.0315 -6.000 -0.4378 0.01357 0.00674 -0.0101 0.5110 0.0320 -5.750 -0.4107 0.01329 0.00644 -0.0097 0.5085 0.0325 -5.500 -0.3835 0.01301 0.00612 -0.0093 0.5059 0.0329 -5.250 -0.3564 0.01274 0.00580 -0.0089 0.5031 0.0333 -5.000 -0.3291 0.01250 0.00551 -0.0085 0.5000 0.0336 -4.500 -0.2752 0.01191 0.00485 -0.0076 0.4944 0.0345 -4.250 -0.2481 0.01159 0.00453 -0.0072 0.4924 0.0352 -4.000 -0.2204 0.01136 0.00431 -0.0068 0.4902 0.0359 -3.750 -0.1926 0.01117 0.00410 -0.0065 0.4879 0.0367 -3.500 -0.1647 0.01100 0.00391 -0.0063 0.4854 0.0375 -3.250 -0.1368 0.01086 0.00374 -0.0060 0.4826 0.0383 -3.000 -0.1094 0.01067 0.00351 -0.0056 0.4793 0.0395 -2.750 -0.0817 0.01052 0.00337 -0.0053 0.4768 0.0409 -2.500 -0.0535 0.01037 0.00323 -0.0051 0.4752 0.0426 -2.250 -0.0255 0.01020 0.00307 -0.0049 0.4733 0.0447 -2.000 0.0025 0.01004 0.00293 -0.0046 0.4710 0.0475 -1.750 0.0304 0.00988 0.00279 -0.0044 0.4685 0.0519 -1.500 0.0580 0.00973 0.00267 -0.0041 0.4660 0.0597 -1.250 0.0855 0.00959 0.00260 -0.0038 0.4634 0.0746 -1.000 0.1132 0.00955 0.00258 -0.0036 0.4601 0.0884 -0.750 0.1416 0.00948 0.00255 -0.0034 0.4582 0.0969 -0.500 0.1696 0.00937 0.00249 -0.0033 0.4562 0.1058 -0.250 0.1979 0.00929 0.00243 -0.0031 0.4536 0.1131 0.000 0.2260 0.00920 0.00237 -0.0029 0.4505 0.1214 0.250 0.2537 0.00911 0.00231 -0.0027 0.4468 0.1346 0.500 0.2808 0.00905 0.00233 -0.0025 0.4422 0.1663 0.750 0.3089 0.00896 0.00234 -0.0023 0.4399 0.1914 1.000 0.3373 0.00892 0.00234 -0.0022 0.4375 0.2060 1.250 0.3655 0.00888 0.00234 -0.0021 0.4351 0.2198 1.500 0.3935 0.00883 0.00234 -0.0020 0.4324 0.2365 1.750 0.4213 0.00880 0.00235 -0.0019 0.4296 0.2532 2.000 0.4488 0.00880 0.00237 -0.0017 0.4263 0.2712 2.250 0.4761 0.00874 0.00241 -0.0015 0.4237 0.3041 2.500 0.4946 0.00805 0.00240 0.0002 0.4216 0.5402 2.750 0.5017 0.00697 0.00251 0.0049 0.4193 0.9166 3.000 0.5390 0.00710 0.00266 0.0033 0.4159 0.9429 3.250 0.5705 0.00724 0.00278 0.0028 0.4124 0.9545 3.500 0.6094 0.00748 0.00296 0.0007 0.4082 0.9610 3.750 0.6360 0.00759 0.00308 0.0012 0.4058 0.9673 4.000 0.6820 0.00774 0.00322 -0.0024 0.4025 0.9688 4.250 0.7277 0.00792 0.00337 -0.0060 0.3985 0.9705 4.500 0.7726 0.00812 0.00353 -0.0095 0.3941 0.9729 4.750 0.8091 0.00828 0.00366 -0.0112 0.3902 0.9752 5.000 0.8421 0.00839 0.00377 -0.0122 0.3866 0.9782 5.250 0.8756 0.00854 0.00390 -0.0133 0.3814 0.9812 5.500 0.9142 0.00869 0.00399 -0.0157 0.3748 0.9822 5.750 0.9509 0.00875 0.00407 -0.0175 0.3709 0.9832 6.000 0.9845 0.00885 0.00415 -0.0188 0.3655 0.9841 6.250 1.0160 0.00900 0.00426 -0.0197 0.3596 0.9850 6.500 1.0496 0.00909 0.00436 -0.0210 0.3546 0.9862 6.750 1.0814 0.00922 0.00448 -0.0220 0.3485 0.9874 7.000 1.1104 0.00941 0.00463 -0.0225 0.3422 0.9886 7.250 1.1395 0.00953 0.00476 -0.0229 0.3364 0.9896 7.500 1.1683 0.00976 0.00495 -0.0234 0.3286 0.9912 7.750 1.1992 0.00995 0.00514 -0.0243 0.3221 0.9930 8.000 1.2316 0.01015 0.00531 -0.0256 0.3142 0.9937 8.250 1.2671 0.01035 0.00549 -0.0275 0.3068 0.9949 8.500 1.2983 0.01062 0.00573 -0.0287 0.2980 0.9959 8.750 1.3275 0.01086 0.00596 -0.0294 0.2900 0.9968 9.000 1.3546 0.01122 0.00627 -0.0299 0.2809 0.9977 9.250 1.3825 0.01148 0.00652 -0.0304 0.2739 0.9984 9.500 1.4095 0.01187 0.00688 -0.0309 0.2659 0.9992 9.750 1.4378 0.01214 0.00716 -0.0315 0.2611 0.9999 10.000 1.4598 0.01246 0.00748 -0.0310 0.2561 1.0000 10.250 1.4779 0.01288 0.00789 -0.0298 0.2510 1.0000 10.500 1.4964 0.01321 0.00824 -0.0286 0.2470 1.0000 10.750 1.5138 0.01357 0.00861 -0.0273 0.2424 1.0000 11.000 1.5283 0.01403 0.00908 -0.0255 0.2382 1.0000 11.250 1.5389 0.01459 0.00964 -0.0233 0.2339 1.0000 11.500 1.5524 0.01495 0.01005 -0.0213 0.2318 1.0000 11.750 1.5613 0.01542 0.01056 -0.0188 0.2288 1.0000 12.000 1.5513 0.01617 0.01135 -0.0135 0.2261 1.0000 12.250 1.5369 0.01744 0.01266 -0.0088 0.2235 1.0000 12.500 1.5314 0.01898 0.01420 -0.0060 0.2195 1.0000 12.750 1.5391 0.01997 0.01525 -0.0046 0.2163 1.0000 13.000 1.5450 0.02118 0.01650 -0.0032 0.2132 1.0000 13.250 1.5481 0.02268 0.01802 -0.0019 0.2098 1.0000 13.500 1.5476 0.02456 0.01991 -0.0006 0.2059 1.0000 13.750 1.5529 0.02606 0.02146 0.0003 0.2025 1.0000 14.000 1.5590 0.02755 0.02299 0.0011 0.1986 1.0000 14.250 1.5577 0.02971 0.02516 0.0019 0.1936 1.0000 14.500 1.5560 0.03195 0.02743 0.0026 0.1894 1.0000 14.750 1.5607 0.03368 0.02920 0.0031 0.1848 1.0000 15.000 1.5579 0.03611 0.03165 0.0037 0.1795 1.0000 15.250 1.5537 0.03876 0.03431 0.0041 0.1729 1.0000 15.500 1.5469 0.04177 0.03732 0.0044 0.1649 1.0000 15.750 1.5434 0.04449 0.04006 0.0046 0.1583 1.0000 16.000 1.5319 0.04807 0.04362 0.0048 0.1492 1.0000 16.250 1.5198 0.05181 0.04733 0.0048 0.1402 1.0000 16.500 1.5108 0.05530 0.05084 0.0047 0.1338 1.0000 16.750 1.5009 0.05893 0.05447 0.0045 0.1277 1.0000 17.000 1.4959 0.06211 0.05767 0.0043 0.1231 1.0000 17.250 1.4889 0.06556 0.06114 0.0040 0.1186 1.0000 17.500 1.4828 0.06898 0.06457 0.0036 0.1147 1.0000 17.750 1.4817 0.07185 0.06749 0.0033 0.1115 1.0000 18.000 1.4770 0.07516 0.07083 0.0028 0.1078 1.0000 18.250 1.4681 0.07908 0.07477 0.0022 0.1038 1.0000 18.500 1.4689 0.08181 0.07755 0.0017 0.1004 1.0000 18.750 1.4596 0.08584 0.08159 0.0009 0.0952 1.0000 19.000 1.4537 0.08950 0.08527 0.0001 0.0886 1.0000 19.250 1.4399 0.09424 0.09001 -0.0010 0.0804 1.0000