XFOIL Version 6.96 Calculated polar for: GOE 613 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 ------ -------- --------- --------- -------- -------- -------- -10.500 -0.3497 0.11035 0.10874 -0.0329 1.0000 0.0156 -10.250 -0.3519 0.10726 0.10566 -0.0328 1.0000 0.0156 -10.000 -0.3571 0.10413 0.10257 -0.0322 1.0000 0.0156 -9.750 -0.3535 0.09806 0.09650 -0.0362 0.9991 0.0158 -9.500 -0.3345 0.09620 0.09463 -0.0378 0.9982 0.0161 -9.250 -0.3176 0.09343 0.09186 -0.0409 0.9968 0.0165 -9.000 -0.3029 0.08986 0.08829 -0.0448 0.9952 0.0170 -8.750 -0.2936 0.08358 0.08202 -0.0530 0.9919 0.0194 -7.500 -0.2307 0.05351 0.05181 -0.0913 0.9661 0.0204 -7.250 -0.2055 0.05231 0.05058 -0.0934 0.9623 0.0210 -7.000 -0.1755 0.04802 0.04619 -0.0999 0.9591 0.0225 -6.750 -0.1513 0.03831 0.03607 -0.1068 0.9486 0.0243 -6.500 -0.1396 0.03280 0.03033 -0.1089 0.9395 0.0234 -6.250 -0.1231 0.02811 0.02529 -0.1095 0.9306 0.0255 -6.000 -0.0987 0.02821 0.02539 -0.1096 0.9232 0.0262 -5.750 -0.0747 0.02695 0.02399 -0.1098 0.9155 0.0274 -5.500 -0.0496 0.02608 0.02280 -0.1082 0.9067 0.0304 -5.250 -0.0316 0.02381 0.02023 -0.1070 0.8978 0.0304 -5.000 -0.0187 0.02011 0.01623 -0.1052 0.8870 0.0301 -4.750 0.0021 0.01890 0.01477 -0.1038 0.8763 0.0304 -4.500 0.0235 0.01765 0.01326 -0.1026 0.8661 0.0305 -4.250 0.0426 0.01534 0.01063 -0.1011 0.8557 0.0306 -4.000 0.0657 0.01427 0.00940 -0.1001 0.8454 0.0306 -3.750 0.0898 0.01336 0.00833 -0.0993 0.8356 0.0305 -3.500 0.1131 0.01196 0.00673 -0.0984 0.8254 0.0307 -3.250 0.1366 0.01064 0.00526 -0.0975 0.8137 0.0311 -3.000 0.1609 0.00994 0.00450 -0.0968 0.8015 0.0321 -2.750 0.1857 0.00959 0.00408 -0.0961 0.7885 0.0326 -2.500 0.2106 0.00931 0.00373 -0.0953 0.7759 0.0332 -2.250 0.2354 0.00906 0.00342 -0.0946 0.7634 0.0337 -2.000 0.2601 0.00882 0.00310 -0.0938 0.7512 0.0342 -1.750 0.2849 0.00857 0.00281 -0.0931 0.7395 0.0347 -1.500 0.3098 0.00838 0.00256 -0.0924 0.7279 0.0353 -1.250 0.3345 0.00822 0.00235 -0.0916 0.7158 0.0359 -1.000 0.3594 0.00811 0.00218 -0.0909 0.7031 0.0369 -0.750 0.3846 0.00807 0.00209 -0.0902 0.6899 0.0378 -0.500 0.4096 0.00801 0.00198 -0.0895 0.6750 0.0382 -0.250 0.4331 0.00776 0.00164 -0.0885 0.6574 0.0401 0.000 0.4568 0.00772 0.00152 -0.0876 0.6333 0.0418 0.250 0.4795 0.00779 0.00145 -0.0864 0.5991 0.0437 0.500 0.5014 0.00792 0.00143 -0.0851 0.5625 0.0459 0.750 0.5247 0.00805 0.00143 -0.0841 0.5371 0.0481 1.000 0.5486 0.00809 0.00140 -0.0833 0.5184 0.0565 1.250 0.5681 0.00754 0.00146 -0.0819 0.5034 0.3227 1.500 0.6242 0.00623 0.00180 -0.0885 0.4844 0.9823 1.750 0.6854 0.00647 0.00191 -0.0960 0.4643 0.9972 2.000 0.7246 0.00663 0.00196 -0.0986 0.4444 1.0000 2.250 0.7457 0.00678 0.00201 -0.0972 0.4272 1.0000 2.500 0.7665 0.00694 0.00208 -0.0958 0.4089 1.0000 3.000 0.8084 0.00730 0.00226 -0.0930 0.3750 1.0000 3.250 0.8296 0.00748 0.00236 -0.0916 0.3601 1.0000 3.500 0.8507 0.00767 0.00247 -0.0902 0.3467 1.0000 4.000 0.8935 0.00805 0.00272 -0.0876 0.3197 1.0000 4.250 0.9152 0.00824 0.00285 -0.0864 0.3077 1.0000 4.500 0.9370 0.00842 0.00299 -0.0852 0.2975 1.0000 4.750 0.9585 0.00863 0.00313 -0.0840 0.2858 1.0000 5.000 0.9808 0.00880 0.00327 -0.0829 0.2766 1.0000 5.250 1.0031 0.00897 0.00341 -0.0818 0.2687 1.0000 5.500 1.0251 0.00917 0.00358 -0.0807 0.2599 1.0000 5.750 1.0474 0.00935 0.00373 -0.0796 0.2505 1.0000 6.000 1.0689 0.00957 0.00390 -0.0784 0.2399 1.0000 6.250 1.0900 0.00982 0.00409 -0.0772 0.2277 1.0000 6.500 1.1107 0.01008 0.00430 -0.0759 0.2142 1.0000 6.750 1.1307 0.01040 0.00453 -0.0745 0.1956 1.0000 7.000 1.1449 0.01105 0.00491 -0.0721 0.1530 1.0000 7.250 1.1478 0.01240 0.00578 -0.0678 0.0799 1.0000 7.500 1.1505 0.01380 0.00683 -0.0634 0.0179 1.0000 7.750 1.1688 0.01415 0.00721 -0.0617 0.0160 1.0000 8.000 1.1857 0.01451 0.00761 -0.0597 0.0150 1.0000 8.250 1.2015 0.01492 0.00807 -0.0576 0.0140 1.0000 8.500 1.2150 0.01549 0.00869 -0.0551 0.0128 1.0000 8.750 1.2297 0.01601 0.00928 -0.0528 0.0122 1.0000 9.000 1.2457 0.01645 0.00976 -0.0509 0.0119 1.0000 9.250 1.2613 0.01693 0.01029 -0.0489 0.0114 1.0000 9.500 1.2759 0.01748 0.01088 -0.0469 0.0110 1.0000 9.750 1.2891 0.01811 0.01157 -0.0447 0.0105 1.0000 10.000 1.3014 0.01881 0.01232 -0.0425 0.0101 1.0000 10.250 1.3113 0.01965 0.01322 -0.0400 0.0097 1.0000 10.500 1.3172 0.02074 0.01440 -0.0370 0.0095 1.0000 10.750 1.3143 0.02239 0.01618 -0.0332 0.0092 1.0000 11.000 1.3293 0.02301 0.01684 -0.0318 0.0090 1.0000 11.250 1.3374 0.02407 0.01797 -0.0297 0.0088 1.0000 11.500 1.3483 0.02500 0.01896 -0.0280 0.0085 1.0000 11.750 1.3545 0.02628 0.02032 -0.0260 0.0084 1.0000 12.000 1.3607 0.02762 0.02173 -0.0242 0.0081 1.0000 12.250 1.3646 0.02922 0.02341 -0.0224 0.0079 1.0000 12.500 1.3684 0.03090 0.02516 -0.0208 0.0077 1.0000 12.750 1.3722 0.03268 0.02701 -0.0194 0.0075 1.0000 13.000 1.3721 0.03489 0.02931 -0.0181 0.0074 1.0000 13.250 1.3726 0.03717 0.03167 -0.0171 0.0073 1.0000 13.500 1.3703 0.03985 0.03443 -0.0163 0.0071 1.0000 13.750 1.3684 0.04260 0.03726 -0.0157 0.0071 1.0000 14.000 1.3641 0.04575 0.04050 -0.0153 0.0070 1.0000 14.250 1.3526 0.04981 0.04465 -0.0150 0.0069 1.0000 14.500 1.3423 0.05384 0.04877 -0.0149 0.0068 1.0000 14.750 1.3324 0.05780 0.05280 -0.0147 0.0067 1.0000 15.000 1.3276 0.06121 0.05628 -0.0145 0.0067 1.0000 15.250 1.3274 0.06451 0.05968 -0.0152 0.0066 1.0000 15.500 1.3261 0.06794 0.06320 -0.0159 0.0066 1.0000 15.750 1.3251 0.07159 0.06696 -0.0170 0.0064 1.0000 16.000 1.3220 0.07509 0.07054 -0.0174 0.0064 1.0000 16.250 1.3192 0.07869 0.07422 -0.0180 0.0064 1.0000 16.500 1.3168 0.08217 0.07778 -0.0185 0.0064 1.0000 16.750 1.3130 0.08647 0.08220 -0.0202 0.0062 1.0000 17.000 1.3096 0.09046 0.08628 -0.0215 0.0061 1.0000 17.250 1.3061 0.09415 0.09005 -0.0221 0.0060 1.0000 17.500 1.3020 0.09838 0.09438 -0.0236 0.0059 1.0000 17.750 1.2982 0.10262 0.09870 -0.0252 0.0058 1.0000 18.000 1.2939 0.10690 0.10307 -0.0268 0.0056 1.0000 18.250 1.2898 0.11105 0.10730 -0.0282 0.0056 1.0000 18.500 1.2857 0.11502 0.11138 -0.0292 0.0056 1.0000 18.750 1.2815 0.11960 0.11604 -0.0314 0.0055 1.0000 19.000 1.2773 0.12406 0.12058 -0.0334 0.0054 1.0000