XFOIL Version 6.96 Calculated polar for: GOE 493 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 ------ -------- --------- --------- -------- -------- -------- -17.250 -0.8278 0.08508 0.08209 -0.0746 1.0000 0.0113 -17.000 -0.8431 0.07933 0.07625 -0.0774 1.0000 0.0114 -16.750 -0.8602 0.07358 0.07041 -0.0801 1.0000 0.0114 -16.500 -0.8751 0.06822 0.06496 -0.0826 1.0000 0.0114 -16.250 -0.8929 0.06281 0.05945 -0.0851 1.0000 0.0115 -16.000 -0.9078 0.05796 0.05451 -0.0871 1.0000 0.0115 -15.750 -0.9205 0.05355 0.05000 -0.0888 1.0000 0.0116 -15.500 -0.9347 0.04924 0.04560 -0.0902 1.0000 0.0116 -15.250 -0.9472 0.04544 0.04172 -0.0911 1.0000 0.0116 -15.000 -0.9629 0.04174 0.03793 -0.0914 1.0000 0.0117 -14.750 -0.9799 0.03861 0.03472 -0.0906 1.0000 0.0117 -14.500 -0.9777 0.03456 0.03054 -0.0949 0.9986 0.0118 -14.250 -0.9736 0.02983 0.02566 -0.1011 0.9955 0.0122 -14.000 -0.9602 0.02701 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0.250 0.4345 0.00640 0.00148 -0.0967 0.6564 0.5632 0.500 0.4606 0.00641 0.00151 -0.0963 0.6484 0.5762 0.750 0.4856 0.00646 0.00154 -0.0957 0.6407 0.5897 1.000 0.5116 0.00645 0.00158 -0.0953 0.6333 0.6040 1.250 0.5362 0.00649 0.00162 -0.0946 0.6257 0.6191 1.500 0.5617 0.00648 0.00167 -0.0942 0.6185 0.6363 1.750 0.5859 0.00651 0.00173 -0.0934 0.6107 0.6569 2.000 0.6105 0.00650 0.00180 -0.0927 0.6034 0.6801 2.250 0.6343 0.00653 0.00187 -0.0919 0.5957 0.7050 2.500 0.6583 0.00654 0.00195 -0.0911 0.5891 0.7314 3.000 0.7047 0.00659 0.00212 -0.0891 0.5732 0.7841 3.250 0.7266 0.00663 0.00221 -0.0878 0.5634 0.8096 3.500 0.7486 0.00664 0.00230 -0.0865 0.5535 0.8379 3.750 0.7690 0.00667 0.00240 -0.0849 0.5435 0.8726 4.000 0.7987 0.00672 0.00256 -0.0853 0.5292 0.9271 4.250 0.8608 0.00695 0.00278 -0.0931 0.5125 0.9638 4.500 0.9111 0.00718 0.00296 -0.0983 0.4967 0.9852 4.750 0.9430 0.00742 0.00314 -0.0995 0.4775 1.0000 5.000 0.9586 0.00763 0.00327 -0.0970 0.4571 1.0000 5.250 0.9726 0.00790 0.00343 -0.0942 0.4347 1.0000 5.500 0.9864 0.00817 0.00361 -0.0914 0.4108 1.0000 5.750 0.9953 0.00850 0.00381 -0.0876 0.3847 1.0000 6.000 1.0060 0.00884 0.00404 -0.0843 0.3604 1.0000 6.250 1.0168 0.00924 0.00431 -0.0810 0.3353 1.0000 6.500 1.0298 0.00962 0.00460 -0.0782 0.3139 1.0000 6.750 1.0428 0.01003 0.00490 -0.0755 0.2916 1.0000 7.000 1.0560 0.01048 0.00523 -0.0729 0.2662 1.0000 7.250 1.0634 0.01117 0.00570 -0.0694 0.2218 1.0000 7.500 1.0588 0.01240 0.00654 -0.0641 0.1537 1.0000 7.750 1.0647 0.01328 0.00722 -0.0606 0.1172 1.0000 8.000 1.0682 0.01433 0.00802 -0.0569 0.0752 1.0000 8.250 1.0753 0.01526 0.00879 -0.0539 0.0488 1.0000 8.500 1.0887 0.01592 0.00940 -0.0519 0.0406 1.0000 8.750 1.1040 0.01650 0.00998 -0.0503 0.0377 1.0000 9.000 1.1185 0.01715 0.01063 -0.0486 0.0351 1.0000 9.250 1.1343 0.01774 0.01125 -0.0471 0.0339 1.0000 9.500 1.1505 0.01833 0.01187 -0.0457 0.0327 1.0000 9.750 1.1657 0.01899 0.01256 -0.0443 0.0318 1.0000 10.000 1.1793 0.01976 0.01335 -0.0428 0.0303 1.0000 10.250 1.1911 0.02066 0.01428 -0.0410 0.0293 1.0000 10.500 1.2026 0.02162 0.01529 -0.0394 0.0284 1.0000 10.750 1.2176 0.02237 0.01608 -0.0382 0.0279 1.0000 11.000 1.2313 0.02321 0.01697 -0.0369 0.0273 1.0000 11.250 1.2444 0.02412 0.01792 -0.0356 0.0266 1.0000 11.500 1.2571 0.02508 0.01891 -0.0344 0.0258 1.0000 11.750 1.2685 0.02614 0.02000 -0.0331 0.0250 1.0000 12.000 1.2759 0.02752 0.02142 -0.0315 0.0243 1.0000 12.250 1.2766 0.02945 0.02343 -0.0295 0.0236 1.0000 12.500 1.2893 0.03052 0.02455 -0.0285 0.0232 1.0000 12.750 1.3037 0.03148 0.02555 -0.0278 0.0226 1.0000 13.000 1.3152 0.03267 0.02679 -0.0269 0.0220 1.0000 13.250 1.3250 0.03405 0.02821 -0.0259 0.0214 1.0000 13.500 1.3348 0.03545 0.02965 -0.0250 0.0209 1.0000 13.750 1.3435 0.03698 0.03122 -0.0242 0.0204 1.0000 14.000 1.3472 0.03899 0.03327 -0.0231 0.0199 1.0000 14.250 1.3420 0.04185 0.03622 -0.0218 0.0193 1.0000 14.500 1.3540 0.04321 0.03763 -0.0213 0.0190 1.0000 14.750 1.3634 0.04483 0.03931 -0.0208 0.0186 1.0000 15.000 1.3722 0.04653 0.04107 -0.0204 0.0181 1.0000 15.250 1.3799 0.04835 0.04294 -0.0200 0.0177 1.0000 15.500 1.3863 0.05034 0.04498 -0.0195 0.0172 1.0000 15.750 1.3910 0.05254 0.04724 -0.0192 0.0169 1.0000 16.000 1.3973 0.05460 0.04933 -0.0189 0.0164 1.0000 16.250 1.3973 0.05739 0.05217 -0.0186 0.0160 1.0000 16.500 1.3889 0.06110 0.05597 -0.0183 0.0156 1.0000 16.750 1.3967 0.06311 0.05805 -0.0183 0.0154 1.0000 17.000 1.4010 0.06554 0.06055 -0.0183 0.0150 1.0000 17.250 1.4031 0.06824 0.06333 -0.0183 0.0148 1.0000 17.500 1.4042 0.07110 0.06626 -0.0185 0.0145 1.0000 17.750 1.4075 0.07370 0.06893 -0.0187 0.0142 1.0000 18.000 1.4083 0.07664 0.07193 -0.0189 0.0139 1.0000 18.250 1.4084 0.07971 0.07507 -0.0193 0.0137 1.0000 18.500 1.4083 0.08287 0.07828 -0.0198 0.0134 1.0000 18.750 1.4043 0.08653 0.08201 -0.0204 0.0131 1.0000 19.000 1.3964 0.09071 0.08626 -0.0211 0.0128 1.0000