XFOIL Version 6.96 Calculated polar for: GOE 512 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.000 -0.4596 0.09880 0.09667 -0.0774 0.9891 0.0084 -14.750 -0.5267 0.08270 0.08042 -0.0875 0.9878 0.0084 -14.500 -0.8059 0.03675 0.03373 -0.1232 0.9754 0.0076 -14.250 -0.8099 0.03048 0.02716 -0.1259 0.9736 0.0076 -14.000 -0.8088 0.02781 0.02431 -0.1239 0.9688 0.0076 -13.750 -0.7955 0.02609 0.02245 -0.1232 0.9663 0.0077 -13.500 -0.7773 0.02474 0.02097 -0.1229 0.9645 0.0078 -13.250 -0.7582 0.02323 0.01932 -0.1228 0.9630 0.0079 -13.000 -0.7363 0.02177 0.01773 -0.1231 0.9617 0.0081 -12.750 -0.7112 0.02058 0.01643 -0.1237 0.9608 0.0083 -12.500 -0.7069 0.01995 0.01572 -0.1195 0.9552 0.0085 -12.250 -0.6857 0.01912 0.01480 -0.1187 0.9527 0.0087 -12.000 -0.6599 0.01835 0.01395 -0.1189 0.9507 0.0089 -11.750 -0.6329 0.01759 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0.2169 0.00968 0.00242 -0.0725 0.4682 0.0566 -2.000 0.2359 0.00971 0.00238 -0.0705 0.4511 0.0604 -1.500 0.2768 0.00973 0.00231 -0.0672 0.4280 0.0685 -1.250 0.2972 0.00972 0.00228 -0.0655 0.4194 0.0765 -1.000 0.3186 0.00968 0.00224 -0.0640 0.4130 0.0862 -0.750 0.3375 0.00953 0.00221 -0.0621 0.4076 0.1277 -0.500 0.3577 0.00949 0.00221 -0.0604 0.4027 0.1523 -0.250 0.3788 0.00943 0.00221 -0.0589 0.3985 0.1737 0.000 0.3994 0.00939 0.00228 -0.0574 0.3935 0.2151 0.250 0.4212 0.00947 0.00234 -0.0560 0.3876 0.2300 0.500 0.4440 0.00952 0.00240 -0.0549 0.3826 0.2391 0.750 0.4670 0.00959 0.00244 -0.0538 0.3781 0.2447 1.000 0.4890 0.00966 0.00250 -0.0525 0.3730 0.2485 1.250 0.5113 0.00974 0.00256 -0.0513 0.3685 0.2531 1.500 0.5344 0.00982 0.00262 -0.0503 0.3638 0.2579 1.750 0.5567 0.00989 0.00267 -0.0491 0.3585 0.2603 2.000 0.5784 0.00999 0.00275 -0.0478 0.3530 0.2643 2.250 0.6012 0.01006 0.00282 -0.0468 0.3479 0.2673 2.500 0.6231 0.01016 0.00289 -0.0455 0.3411 0.2701 2.750 0.6445 0.01027 0.00297 -0.0442 0.3347 0.2711 3.000 0.6661 0.01038 0.00304 -0.0430 0.3269 0.2721 3.250 0.6867 0.01050 0.00314 -0.0415 0.3187 0.2743 3.500 0.7073 0.01063 0.00323 -0.0401 0.3090 0.2757 3.750 0.7275 0.01079 0.00336 -0.0387 0.2980 0.2782 4.000 0.7470 0.01097 0.00349 -0.0371 0.2875 0.2804 4.250 0.7660 0.01117 0.00364 -0.0354 0.2763 0.2824 4.500 0.7858 0.01135 0.00378 -0.0339 0.2679 0.2835 4.750 0.8047 0.01156 0.00395 -0.0323 0.2588 0.2847 5.000 0.8249 0.01173 0.00410 -0.0309 0.2524 0.2855 5.250 0.8439 0.01194 0.00427 -0.0294 0.2453 0.2871 5.500 0.8634 0.01211 0.00444 -0.0279 0.2407 0.2888 5.750 0.8832 0.01227 0.00461 -0.0265 0.2367 0.2904 6.000 0.9027 0.01246 0.00479 -0.0251 0.2327 0.2923 6.250 0.9215 0.01268 0.00500 -0.0235 0.2279 0.2942 6.500 0.9416 0.01285 0.00519 -0.0222 0.2257 0.2962 6.750 0.9613 0.01303 0.00539 -0.0209 0.2230 0.2982 7.000 0.9808 0.01322 0.00559 -0.0196 0.2207 0.3000 7.250 0.9996 0.01344 0.00582 -0.0181 0.2175 0.3023 7.500 1.0185 0.01365 0.00605 -0.0167 0.2153 0.3056 7.750 1.0369 0.01389 0.00631 -0.0153 0.2130 0.3095 8.000 1.0548 0.01414 0.00658 -0.0137 0.2107 0.3131 8.250 1.0739 0.01434 0.00683 -0.0125 0.2097 0.3206 8.500 1.0936 0.01453 0.00708 -0.0113 0.2080 0.3282 8.750 1.1118 0.01472 0.00736 -0.0099 0.2065 0.3610 9.250 1.3083 0.01484 0.00889 -0.0429 0.1961 0.9931 9.500 1.3319 0.01521 0.00928 -0.0428 0.1934 0.9968 9.750 1.3640 0.01555 0.00965 -0.0445 0.1910 0.9986 10.000 1.3930 0.01597 0.01007 -0.0456 0.1854 0.9996 10.250 1.4132 0.01644 0.01052 -0.0451 0.1806 1.0000 10.500 1.4283 0.01679 0.01090 -0.0432 0.1774 1.0000 10.750 1.4421 0.01721 0.01132 -0.0413 0.1720 1.0000 11.000 1.4538 0.01777 0.01184 -0.0391 0.1648 1.0000 11.250 1.4656 0.01832 0.01238 -0.0370 0.1570 1.0000 11.500 1.4714 0.01921 0.01318 -0.0341 0.1422 1.0000 11.750 1.4699 0.02052 0.01437 -0.0305 0.1227 1.0000 12.000 1.4763 0.02147 0.01530 -0.0280 0.1153 1.0000 12.250 1.4802 0.02261 0.01642 -0.0253 0.1063 1.0000 12.500 1.4845 0.02379 0.01758 -0.0229 0.0974 1.0000 12.750 1.4846 0.02529 0.01904 -0.0201 0.0859 1.0000 13.000 1.4628 0.02836 0.02193 -0.0156 0.0573 1.0000 13.250 1.4332 0.03238 0.02583 -0.0113 0.0269 1.0000 13.500 1.4248 0.03507 0.02852 -0.0091 0.0169 1.0000 13.750 1.4260 0.03709 0.03059 -0.0078 0.0144 1.0000 14.000 1.4274 0.03917 0.03273 -0.0067 0.0128 1.0000 14.250 1.4291 0.04130 0.03493 -0.0057 0.0117 1.0000 14.500 1.4322 0.04338 0.03707 -0.0050 0.0114 1.0000 14.750 1.4327 0.04578 0.03954 -0.0043 0.0104 1.0000 15.000 1.4328 0.04829 0.04212 -0.0038 0.0100 1.0000 15.250 1.4315 0.05100 0.04489 -0.0034 0.0095 1.0000 15.500 1.4297 0.05383 0.04781 -0.0031 0.0089 1.0000 15.750 1.4271 0.05682 0.05088 -0.0029 0.0087 1.0000 16.000 1.4244 0.05992 0.05405 -0.0028 0.0085 1.0000 16.250 1.4199 0.06326 0.05748 -0.0029 0.0082 1.0000 16.500 1.4142 0.06684 0.06114 -0.0032 0.0079 1.0000 16.750 1.4064 0.07078 0.06517 -0.0035 0.0076 1.0000 17.000 1.3983 0.07485 0.06933 -0.0041 0.0074 1.0000 17.250 1.3899 0.07899 0.07356 -0.0047 0.0072 1.0000 17.500 1.3805 0.08333 0.07799 -0.0055 0.0070 1.0000 17.750 1.3719 0.08763 0.08238 -0.0063 0.0068 1.0000 18.000 1.3614 0.09222 0.08706 -0.0073 0.0069 1.0000 18.250 1.3529 0.09657 0.09150 -0.0083 0.0066 1.0000 18.500 1.3421 0.10129 0.09632 -0.0094 0.0063 1.0000 18.750 1.3310 0.10612 0.10124 -0.0107 0.0062 1.0000