XFOIL Version 6.96 Calculated polar for: GOE 670 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.3523 0.09462 0.09249 -0.0338 1.0000 0.0336 -9.750 -0.3467 0.09308 0.09096 -0.0319 0.9998 0.0341 -9.500 -0.4320 0.09347 0.09120 -0.0364 1.0000 0.0335 -9.250 -0.4321 0.09206 0.08982 -0.0339 1.0000 0.0339 -9.000 -0.4354 0.09069 0.08847 -0.0315 1.0000 0.0343 -8.750 -0.4357 0.08952 0.08732 -0.0295 0.9999 0.0348 -8.500 -0.4206 0.08637 0.08417 -0.0328 0.9981 0.0358 -8.250 -0.4077 0.08226 0.08006 -0.0381 0.9953 0.0374 -8.000 -0.3972 0.07174 0.06948 -0.0584 0.9863 0.0404 -7.750 -0.3942 0.05960 0.05720 -0.0706 0.9808 0.0410 -7.500 -0.3779 0.05810 0.05570 -0.0709 0.9773 0.0418 -7.250 -0.3725 0.04096 0.03798 -0.0832 0.9715 0.0413 -7.000 -0.3497 0.03946 0.03644 -0.0844 0.9686 0.0420 -6.750 -0.3617 0.02459 0.02037 -0.0844 0.9598 0.0378 -6.500 -0.3355 0.02125 0.01652 -0.0854 0.9581 0.0385 -6.250 -0.3040 0.01938 0.01431 -0.0868 0.9570 0.0394 -6.000 -0.2817 0.01856 0.01328 -0.0858 0.9522 0.0401 -5.750 -0.2530 0.01787 0.01240 -0.0860 0.9491 0.0405 -5.500 -0.2262 0.01552 0.00975 -0.0864 0.9469 0.0415 -5.250 -0.1949 0.01446 0.00859 -0.0873 0.9452 0.0426 -5.000 -0.1621 0.01381 0.00789 -0.0884 0.9437 0.0437 -4.750 -0.1282 0.01328 0.00731 -0.0896 0.9422 0.0451 -4.500 -0.1055 0.01288 0.00685 -0.0885 0.9371 0.0463 -4.250 -0.0777 0.01238 0.00628 -0.0884 0.9334 0.0474 -4.000 -0.0471 0.01192 0.00576 -0.0888 0.9307 0.0487 -3.750 -0.0156 0.01141 0.00518 -0.0895 0.9284 0.0500 -3.500 0.0108 0.01080 0.00457 -0.0891 0.9247 0.0528 -3.250 0.0351 0.01055 0.00432 -0.0882 0.9193 0.0553 -3.000 0.0647 0.01029 0.00404 -0.0884 0.9155 0.0587 -2.750 0.0953 0.00986 0.00361 -0.0888 0.9120 0.0636 -2.500 0.1184 0.00968 0.00345 -0.0876 0.9048 0.0694 -2.250 0.1476 0.00938 0.00318 -0.0876 0.8988 0.0782 -2.000 0.1738 0.00922 0.00303 -0.0870 0.8922 0.0880 -1.750 0.2014 0.00912 0.00292 -0.0868 0.8853 0.0977 -1.500 0.2281 0.00892 0.00275 -0.0863 0.8778 0.1077 -1.250 0.2549 0.00877 0.00257 -0.0858 0.8684 0.1154 -1.000 0.2799 0.00859 0.00241 -0.0849 0.8575 0.1239 -0.750 0.3061 0.00844 0.00224 -0.0843 0.8464 0.1322 -0.500 0.3322 0.00830 0.00210 -0.0837 0.8343 0.1422 -0.250 0.3575 0.00815 0.00196 -0.0830 0.8208 0.1548 0.000 0.3823 0.00800 0.00186 -0.0821 0.8063 0.1760 0.250 0.4048 0.00764 0.00183 -0.0810 0.7922 0.2853 0.500 0.4070 0.00603 0.00190 -0.0756 0.7775 0.8372 0.750 0.4979 0.00610 0.00212 -0.0887 0.7618 0.9747 1.000 0.5473 0.00624 0.00214 -0.0932 0.7387 0.9882 1.250 0.5979 0.00638 0.00213 -0.0981 0.7128 0.9974 1.500 0.6300 0.00650 0.00210 -0.0990 0.6886 1.0000 1.750 0.6502 0.00663 0.00212 -0.0973 0.6689 1.0000 2.000 0.6709 0.00677 0.00215 -0.0957 0.6518 1.0000 2.250 0.6917 0.00691 0.00221 -0.0942 0.6349 1.0000 2.500 0.7124 0.00707 0.00228 -0.0926 0.6175 1.0000 2.750 0.7329 0.00723 0.00237 -0.0910 0.5986 1.0000 3.000 0.7527 0.00741 0.00245 -0.0893 0.5755 1.0000 3.250 0.7724 0.00758 0.00254 -0.0875 0.5484 1.0000 3.500 0.7904 0.00782 0.00263 -0.0854 0.5062 1.0000 3.750 0.8033 0.00830 0.00280 -0.0823 0.4413 1.0000 4.000 0.8170 0.00885 0.00306 -0.0795 0.3847 1.0000 4.250 0.8331 0.00933 0.00332 -0.0772 0.3394 1.0000 4.500 0.8504 0.00976 0.00356 -0.0751 0.3063 1.0000 4.750 0.8696 0.01009 0.00381 -0.0734 0.2854 1.0000 5.000 0.8891 0.01041 0.00405 -0.0718 0.2695 1.0000 5.250 0.9088 0.01073 0.00428 -0.0702 0.2542 1.0000 5.500 0.9288 0.01103 0.00452 -0.0686 0.2418 1.0000 5.750 0.9491 0.01131 0.00477 -0.0672 0.2324 1.0000 6.000 0.9703 0.01153 0.00500 -0.0659 0.2245 1.0000 6.250 0.9900 0.01185 0.00526 -0.0643 0.2149 1.0000 6.500 1.0119 0.01203 0.00548 -0.0631 0.2065 1.0000 6.750 1.0323 0.01230 0.00574 -0.0617 0.1971 1.0000 7.000 1.0525 0.01258 0.00599 -0.0603 0.1857 1.0000 7.250 1.0733 0.01284 0.00623 -0.0590 0.1719 1.0000 7.500 1.0921 0.01322 0.00650 -0.0573 0.1446 1.0000 7.750 1.0995 0.01435 0.00718 -0.0540 0.0805 1.0000 8.000 1.1062 0.01558 0.00809 -0.0503 0.0358 1.0000 8.250 1.1190 0.01630 0.00881 -0.0476 0.0301 1.0000 8.500 1.1338 0.01684 0.00941 -0.0452 0.0276 1.0000 8.750 1.1466 0.01753 0.01014 -0.0426 0.0256 1.0000 9.000 1.1563 0.01841 0.01110 -0.0395 0.0239 1.0000 9.250 1.1711 0.01897 0.01173 -0.0374 0.0228 1.0000 9.500 1.1843 0.01963 0.01244 -0.0350 0.0216 1.0000 9.750 1.1961 0.02039 0.01325 -0.0326 0.0207 1.0000 10.000 1.2044 0.02138 0.01429 -0.0297 0.0198 1.0000 10.250 1.2043 0.02294 0.01593 -0.0258 0.0190 1.0000 10.500 1.2158 0.02378 0.01686 -0.0236 0.0187 1.0000 10.750 1.2270 0.02466 0.01782 -0.0215 0.0181 1.0000 11.000 1.2355 0.02576 0.01900 -0.0192 0.0176 1.0000 11.250 1.2462 0.02670 0.02001 -0.0172 0.0168 1.0000 11.500 1.2542 0.02789 0.02125 -0.0151 0.0163 1.0000 11.750 1.2611 0.02919 0.02262 -0.0130 0.0159 1.0000 12.000 1.2662 0.03069 0.02417 -0.0109 0.0155 1.0000 12.250 1.2693 0.03252 0.02607 -0.0088 0.0152 1.0000 12.500 1.2704 0.03497 0.02859 -0.0064 0.0148 1.0000 12.750 1.2779 0.03637 0.03011 -0.0049 0.0147 1.0000 13.000 1.2841 0.03798 0.03185 -0.0034 0.0144 1.0000 13.250 1.2893 0.03977 0.03376 -0.0020 0.0141 1.0000 13.500 1.2935 0.04171 0.03582 -0.0007 0.0138 1.0000 13.750 1.2970 0.04382 0.03806 0.0006 0.0136 1.0000 14.000 1.2992 0.04615 0.04052 0.0017 0.0134 1.0000 14.250 1.3005 0.04855 0.04305 0.0026 0.0132 1.0000 14.500 1.3007 0.05110 0.04572 0.0034 0.0130 1.0000 14.750 1.2996 0.05393 0.04869 0.0039 0.0129 1.0000 15.000 1.2986 0.05666 0.05150 0.0041 0.0126 1.0000 15.250 1.2960 0.05972 0.05468 0.0040 0.0124 1.0000 15.500 1.2910 0.06334 0.05845 0.0039 0.0124 1.0000 15.750 1.2855 0.06702 0.06225 0.0033 0.0122 1.0000 16.000 1.2828 0.07035 0.06560 0.0027 0.0118 1.0000 16.250 1.2738 0.07487 0.07027 0.0017 0.0117 1.0000 16.500 1.2613 0.08010 0.07566 0.0005 0.0116 1.0000 16.750 1.2515 0.08500 0.08072 -0.0015 0.0117 1.0000 17.000 1.2318 0.09185 0.08777 -0.0041 0.0116 1.0000 17.250 1.2214 0.09739 0.09345 -0.0070 0.0116 1.0000