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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.500 -0.7567 0.08678 0.08308 -0.0733 1.0000 0.0104 -16.250 -0.7732 0.08088 0.07710 -0.0760 1.0000 0.0104 -16.000 -0.7909 0.07501 0.07114 -0.0786 1.0000 0.0104 -15.750 -0.8085 0.06931 0.06534 -0.0812 1.0000 0.0105 -15.500 -0.8314 0.06321 0.05914 -0.0838 1.0000 0.0104 -15.250 -0.8472 0.05826 0.05409 -0.0857 1.0000 0.0105 -15.000 -0.8668 0.05315 0.04888 -0.0875 1.0000 0.0105 -14.750 -0.8843 0.04870 0.04433 -0.0887 1.0000 0.0105 -14.250 -0.9005 0.03941 0.03481 -0.0955 0.9972 0.0108 -14.000 -0.8945 0.03542 0.03070 -0.1003 0.9926 0.0110 -13.750 -0.8858 0.03212 0.02727 -0.1043 0.9876 0.0112 -13.500 -0.8710 0.02958 0.02462 -0.1080 0.9839 0.0115 -13.250 -0.8591 0.02752 0.02245 -0.1100 0.9772 0.0118 -13.000 -0.8411 0.02571 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0.2247 -3.500 0.0475 0.00900 0.00244 -0.1024 0.7597 0.2432 -3.250 0.0731 0.00887 0.00233 -0.1020 0.7532 0.2644 -3.000 0.0982 0.00871 0.00225 -0.1015 0.7461 0.2902 -2.750 0.1238 0.00860 0.00216 -0.1011 0.7398 0.3156 -2.500 0.1492 0.00848 0.00211 -0.1007 0.7328 0.3389 -2.250 0.1749 0.00841 0.00205 -0.1002 0.7258 0.3610 -2.000 0.2003 0.00832 0.00201 -0.0998 0.7184 0.3843 -1.750 0.2259 0.00826 0.00198 -0.0993 0.7110 0.4059 -1.500 0.2517 0.00822 0.00196 -0.0989 0.7040 0.4244 -1.250 0.2771 0.00820 0.00194 -0.0984 0.6953 0.4416 -1.000 0.3025 0.00818 0.00194 -0.0979 0.6862 0.4587 -0.750 0.3273 0.00819 0.00194 -0.0973 0.6767 0.4776 -0.500 0.3524 0.00817 0.00195 -0.0967 0.6674 0.4965 -0.250 0.3774 0.00818 0.00196 -0.0961 0.6587 0.5130 0.000 0.4022 0.00820 0.00198 -0.0955 0.6487 0.5268 0.250 0.4270 0.00822 0.00201 -0.0949 0.6393 0.5402 0.750 0.4764 0.00829 0.00208 -0.0936 0.6211 0.5670 1.000 0.5008 0.00833 0.00213 -0.0929 0.6135 0.5825 1.250 0.5257 0.00834 0.00219 -0.0923 0.6055 0.5989 1.500 0.5499 0.00838 0.00225 -0.0915 0.5985 0.6143 1.750 0.5749 0.00840 0.00231 -0.0910 0.5918 0.6299 2.250 0.6231 0.00846 0.00247 -0.0894 0.5784 0.6650 2.500 0.6468 0.00849 0.00257 -0.0886 0.5711 0.6860 2.750 0.6698 0.00853 0.00267 -0.0876 0.5642 0.7097 3.000 0.6930 0.00856 0.00278 -0.0866 0.5565 0.7342 3.250 0.7150 0.00862 0.00289 -0.0854 0.5493 0.7595 3.500 0.7375 0.00865 0.00301 -0.0843 0.5410 0.7847 3.750 0.7578 0.00872 0.00313 -0.0827 0.5302 0.8109 4.000 0.7771 0.00879 0.00326 -0.0809 0.5184 0.8416 4.250 0.7998 0.00883 0.00341 -0.0798 0.5063 0.8814 4.500 0.8450 0.00907 0.00368 -0.0838 0.4863 0.9358 4.750 0.8980 0.00943 0.00397 -0.0898 0.4591 0.9954 5.000 0.9158 0.00971 0.00417 -0.0879 0.4402 1.0000 5.250 0.9278 0.00996 0.00434 -0.0848 0.4210 1.0000 5.500 0.9375 0.01031 0.00457 -0.0812 0.3950 1.0000 5.750 0.9478 0.01071 0.00484 -0.0779 0.3693 1.0000 6.000 0.9584 0.01116 0.00516 -0.0748 0.3454 1.0000 6.250 0.9721 0.01156 0.00548 -0.0723 0.3264 1.0000 6.500 0.9863 0.01197 0.00582 -0.0700 0.3088 1.0000 6.750 1.0010 0.01239 0.00618 -0.0677 0.2915 1.0000 7.000 1.0142 0.01289 0.00658 -0.0653 0.2693 1.0000 7.250 1.0252 0.01350 0.00705 -0.0627 0.2388 1.0000 7.500 1.0228 0.01475 0.00791 -0.0581 0.1706 1.0000 7.750 1.0298 0.01565 0.00865 -0.0550 0.1407 1.0000 8.000 1.0380 0.01654 0.00940 -0.0523 0.1117 1.0000 8.250 1.0449 0.01752 0.01022 -0.0495 0.0836 1.0000 8.500 1.0557 0.01833 0.01096 -0.0473 0.0680 1.0000 8.750 1.0671 0.01915 0.01172 -0.0453 0.0543 1.0000 9.000 1.0785 0.01999 0.01251 -0.0434 0.0451 1.0000 9.250 1.0915 0.02076 0.01328 -0.0417 0.0409 1.0000 9.500 1.1054 0.02150 0.01404 -0.0401 0.0386 1.0000 9.750 1.1180 0.02234 0.01489 -0.0385 0.0364 1.0000 10.000 1.1300 0.02323 0.01581 -0.0369 0.0348 1.0000 10.250 1.1433 0.02407 0.01669 -0.0355 0.0338 1.0000 10.500 1.1561 0.02496 0.01764 -0.0342 0.0329 1.0000 10.750 1.1685 0.02590 0.01863 -0.0328 0.0319 1.0000 11.000 1.1796 0.02695 0.01972 -0.0314 0.0309 1.0000 11.250 1.1895 0.02811 0.02091 -0.0300 0.0299 1.0000 11.500 1.1979 0.02941 0.02226 -0.0285 0.0289 1.0000 11.750 1.2057 0.03081 0.02371 -0.0271 0.0282 1.0000 12.000 1.2173 0.03194 0.02491 -0.0261 0.0275 1.0000 12.250 1.2268 0.03326 0.02630 -0.0250 0.0269 1.0000 12.500 1.2363 0.03463 0.02773 -0.0239 0.0262 1.0000 12.750 1.2453 0.03608 0.02924 -0.0229 0.0256 1.0000 13.000 1.2531 0.03765 0.03087 -0.0220 0.0249 1.0000 13.250 1.2599 0.03935 0.03263 -0.0211 0.0242 1.0000 13.500 1.2647 0.04129 0.03461 -0.0202 0.0235 1.0000 13.750 1.2683 0.04339 0.03678 -0.0193 0.0229 1.0000 14.000 1.2789 0.04488 0.03835 -0.0188 0.0222 1.0000 14.250 1.2844 0.04687 0.04042 -0.0182 0.0218 1.0000 14.500 1.2927 0.04864 0.04225 -0.0177 0.0210 1.0000 14.750 1.2989 0.05065 0.04433 -0.0173 0.0204 1.0000 15.000 1.3050 0.05269 0.04644 -0.0170 0.0198 1.0000 15.250 1.3086 0.05505 0.04885 -0.0166 0.0193 1.0000 15.500 1.3110 0.05756 0.05142 -0.0164 0.0188 1.0000 15.750 1.3142 0.06003 0.05397 -0.0162 0.0184 1.0000 16.000 1.3185 0.06242 0.05646 -0.0161 0.0179 1.0000 16.250 1.3228 0.06485 0.05897 -0.0161 0.0173 1.0000 16.500 1.3263 0.06740 0.06160 -0.0162 0.0167 1.0000 16.750 1.3289 0.07009 0.06437 -0.0163 0.0162 1.0000 17.000 1.3323 0.07270 0.06704 -0.0165 0.0157 1.0000 17.250 1.3330 0.07570 0.07011 -0.0168 0.0153 1.0000 17.500 1.3323 0.07892 0.07339 -0.0173 0.0149 1.0000 17.750 1.3323 0.08209 0.07666 -0.0177 0.0146 1.0000 18.000 1.3333 0.08515 0.07981 -0.0182 0.0140 1.0000 18.250 1.3325 0.08847 0.08323 -0.0189 0.0136 1.0000 18.500 1.3322 0.09180 0.08664 -0.0196 0.0132 1.0000 18.750 1.3305 0.09536 0.09028 -0.0205 0.0128 1.0000 19.000 1.3286 0.09900 0.09400 -0.0215 0.0125 1.0000 19.250 1.3256 0.10285 0.09793 -0.0226 0.0122 1.0000