XFOIL Version 6.96 Calculated polar for: GOE 584 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.250 -0.3912 0.14800 0.14543 -0.0316 1.0000 0.0133 -15.000 -0.3846 0.14526 0.14269 -0.0327 1.0000 0.0135 -13.500 -0.9028 0.03169 0.02829 -0.0995 0.9864 0.0184 -13.250 -0.8865 0.02859 0.02491 -0.1020 0.9761 0.0190 -13.000 -0.8634 0.02630 0.02243 -0.1043 0.9668 0.0199 -12.750 -0.8366 0.02451 0.02048 -0.1064 0.9568 0.0210 -12.500 -0.8074 0.02299 0.01875 -0.1084 0.9457 0.0223 -12.250 -0.7771 0.02183 0.01747 -0.1102 0.9326 0.0236 -12.000 -0.7484 0.02097 0.01648 -0.1112 0.9174 0.0252 -11.750 -0.7237 0.02013 0.01545 -0.1113 0.9007 0.0267 -11.500 -0.6984 0.01976 0.01501 -0.1111 0.8857 0.0280 -11.250 -0.6740 0.01943 0.01458 -0.1107 0.8721 0.0294 -11.000 -0.6514 0.01891 0.01389 -0.1099 0.8592 0.0310 -10.750 -0.6280 0.01852 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0.01018 0.00247 -0.0935 0.5974 0.0642 -1.000 0.3847 0.01009 0.00235 -0.0931 0.5910 0.0663 -0.750 0.4113 0.01004 0.00228 -0.0928 0.5848 0.0685 -0.500 0.4383 0.00998 0.00223 -0.0925 0.5785 0.0710 -0.250 0.4649 0.00996 0.00219 -0.0921 0.5726 0.0744 0.000 0.4917 0.00992 0.00216 -0.0919 0.5674 0.0803 0.250 0.5184 0.00986 0.00214 -0.0916 0.5616 0.0922 0.500 0.5442 0.00975 0.00215 -0.0911 0.5559 0.1350 0.750 0.5704 0.00965 0.00218 -0.0908 0.5505 0.1782 1.000 0.5967 0.00959 0.00221 -0.0905 0.5446 0.2111 1.250 0.6224 0.00954 0.00225 -0.0900 0.5387 0.2532 1.500 0.6476 0.00935 0.00232 -0.0896 0.5335 0.3439 1.750 0.6710 0.00904 0.00238 -0.0889 0.5271 0.4785 2.000 0.6825 0.00815 0.00254 -0.0853 0.5218 0.8356 2.500 0.8073 0.00828 0.00278 -0.1002 0.5058 1.0000 2.750 0.8315 0.00838 0.00285 -0.0994 0.4993 1.0000 3.000 0.8552 0.00849 0.00293 -0.0985 0.4921 1.0000 3.250 0.8789 0.00862 0.00302 -0.0976 0.4854 1.0000 3.500 0.9028 0.00873 0.00311 -0.0968 0.4775 1.0000 3.750 0.9261 0.00888 0.00322 -0.0959 0.4702 1.0000 4.000 0.9498 0.00901 0.00333 -0.0950 0.4615 1.0000 4.250 0.9725 0.00918 0.00345 -0.0940 0.4508 1.0000 4.500 0.9943 0.00938 0.00359 -0.0928 0.4378 1.0000 4.750 1.0156 0.00961 0.00374 -0.0915 0.4220 1.0000 5.000 1.0366 0.00985 0.00392 -0.0902 0.4059 1.0000 5.250 1.0570 0.01013 0.00412 -0.0889 0.3889 1.0000 5.500 1.0775 0.01040 0.00433 -0.0875 0.3743 1.0000 5.750 1.0986 0.01066 0.00454 -0.0863 0.3623 1.0000 6.000 1.1192 0.01093 0.00477 -0.0850 0.3499 1.0000 6.250 1.1392 0.01123 0.00502 -0.0836 0.3379 1.0000 6.500 1.1583 0.01156 0.00530 -0.0821 0.3257 1.0000 6.750 1.1779 0.01186 0.00557 -0.0806 0.3143 1.0000 7.000 1.1972 0.01216 0.00585 -0.0792 0.3045 1.0000 7.250 1.2151 0.01251 0.00617 -0.0775 0.2946 1.0000 7.500 1.2336 0.01281 0.00647 -0.0759 0.2847 1.0000 7.750 1.2490 0.01316 0.00680 -0.0737 0.2756 1.0000 8.000 1.2634 0.01354 0.00714 -0.0714 0.2652 1.0000 8.250 1.2774 0.01395 0.00753 -0.0691 0.2534 1.0000 8.500 1.2882 0.01451 0.00802 -0.0664 0.2366 1.0000 8.750 1.2982 0.01515 0.00857 -0.0637 0.2196 1.0000 9.000 1.3084 0.01581 0.00916 -0.0611 0.2038 1.0000 9.250 1.3196 0.01647 0.00978 -0.0588 0.1903 1.0000 9.500 1.3299 0.01721 0.01048 -0.0566 0.1763 1.0000 9.750 1.3397 0.01802 0.01125 -0.0544 0.1630 1.0000 10.000 1.3494 0.01889 0.01208 -0.0523 0.1517 1.0000 10.250 1.3569 0.01993 0.01306 -0.0501 0.1389 1.0000 10.500 1.3663 0.02092 0.01404 -0.0483 0.1292 1.0000 10.750 1.3759 0.02195 0.01507 -0.0466 0.1221 1.0000 11.000 1.3857 0.02302 0.01613 -0.0451 0.1150 1.0000 11.250 1.3941 0.02422 0.01733 -0.0435 0.1090 1.0000 11.500 1.4041 0.02535 0.01849 -0.0422 0.1029 1.0000 11.750 1.4116 0.02669 0.01984 -0.0408 0.0971 1.0000 12.000 1.4205 0.02798 0.02115 -0.0395 0.0912 1.0000 12.250 1.4259 0.02957 0.02273 -0.0382 0.0842 1.0000 12.500 1.4296 0.03134 0.02447 -0.0369 0.0739 1.0000 13.000 1.4168 0.03681 0.02973 -0.0337 0.0366 1.0000 13.250 1.4137 0.03942 0.03234 -0.0325 0.0299 1.0000 13.500 1.4161 0.04162 0.03459 -0.0317 0.0269 1.0000 13.750 1.4178 0.04393 0.03696 -0.0310 0.0246 1.0000 14.000 1.4201 0.04625 0.03934 -0.0304 0.0230 1.0000 14.250 1.4235 0.04850 0.04166 -0.0299 0.0214 1.0000 14.500 1.4257 0.05095 0.04418 -0.0295 0.0204 1.0000 14.750 1.4263 0.05360 0.04690 -0.0292 0.0194 1.0000 15.000 1.4277 0.05624 0.04961 -0.0289 0.0186 1.0000 15.250 1.4298 0.05885 0.05231 -0.0288 0.0179 1.0000 15.500 1.4303 0.06167 0.05521 -0.0288 0.0171 1.0000 15.750 1.4297 0.06469 0.05831 -0.0288 0.0165 1.0000 16.000 1.4272 0.06801 0.06170 -0.0290 0.0159 1.0000 16.250 1.4247 0.07140 0.06517 -0.0293 0.0155 1.0000 16.500 1.4235 0.07467 0.06854 -0.0296 0.0151 1.0000 16.750 1.4212 0.07813 0.07209 -0.0301 0.0146 1.0000 17.000 1.4187 0.08169 0.07574 -0.0307 0.0142 1.0000 17.250 1.4152 0.08544 0.07959 -0.0314 0.0138 1.0000 17.500 1.4104 0.08945 0.08368 -0.0323 0.0134 1.0000 17.750 1.4038 0.09377 0.08808 -0.0333 0.0131 1.0000 18.000 1.3969 0.09822 0.09264 -0.0345 0.0129 1.0000