XFOIL Version 6.96 Calculated polar for: GOE 573 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 ------ -------- --------- --------- -------- -------- -------- -10.750 -0.0016 0.09236 0.08972 -0.1093 0.7751 0.0178 -10.500 0.0723 0.07503 0.07207 -0.1136 0.6788 0.0180 -10.250 0.0826 0.07296 0.06992 -0.1134 0.6644 0.0182 -10.000 0.0883 0.07036 0.06727 -0.1138 0.6525 0.0183 -9.750 0.0970 0.06846 0.06533 -0.1141 0.6414 0.0187 -9.500 0.0999 0.06551 0.06236 -0.1147 0.6336 0.0189 -9.250 0.1056 0.06317 0.05999 -0.1152 0.6245 0.0195 -9.000 0.1078 0.06024 0.05704 -0.1159 0.6167 0.0203 -8.750 0.0924 0.05468 0.05150 -0.1191 0.6137 0.0216 -8.500 0.0888 0.05106 0.04787 -0.1203 0.6075 0.0216 -8.250 0.0821 0.04737 0.04417 -0.1219 0.6020 0.0217 -8.000 0.0715 0.04403 0.04085 -0.1233 0.5969 0.0217 -7.750 0.0538 0.04062 0.03742 -0.1222 0.5917 0.0217 -7.500 0.0332 0.03539 0.03215 -0.1218 0.5879 0.0220 -7.250 0.0380 0.03348 0.03021 -0.1208 0.5813 0.0222 -7.000 0.0467 0.03213 0.02881 -0.1198 0.5739 0.0225 -6.750 0.0534 0.03005 0.02667 -0.1190 0.5680 0.0227 -6.500 0.0612 0.02806 0.02461 -0.1181 0.5612 0.0233 -6.250 0.0685 0.02573 0.02219 -0.1171 0.5552 0.0244 -5.500 0.0665 0.01361 0.00932 -0.1089 0.5417 0.0271 -5.250 0.0805 0.02650 0.02186 -0.1112 0.5433 0.0274 -5.000 0.1000 0.02609 0.02140 -0.1101 0.5361 0.0281 -4.750 0.1173 0.02504 0.02022 -0.1083 0.5288 0.0295 -4.500 0.1328 0.02336 0.01807 -0.1047 0.5228 0.0317 -4.250 0.1251 0.01724 0.01145 -0.0984 0.5187 0.0284 -4.000 0.1455 0.01661 0.01066 -0.0969 0.5111 0.0292 -3.750 0.1650 0.01539 0.00921 -0.0951 0.5047 0.0296 -3.500 0.1858 0.01437 0.00796 -0.0935 0.4977 0.0298 -3.250 0.2084 0.01367 0.00711 -0.0923 0.4917 0.0303 -3.000 0.2322 0.01315 0.00646 -0.0914 0.4857 0.0307 -2.750 0.2558 0.01293 0.00612 -0.0904 0.4796 0.0313 -2.500 0.2804 0.01279 0.00590 -0.0896 0.4749 0.0317 -2.250 0.3043 0.01188 0.00488 -0.0888 0.4701 0.0321 -2.000 0.3275 0.01137 0.00430 -0.0879 0.4653 0.0326 -1.750 0.3511 0.01106 0.00396 -0.0870 0.4613 0.0332 -1.500 0.3751 0.01083 0.00372 -0.0861 0.4577 0.0337 -1.250 0.3987 0.01066 0.00352 -0.0852 0.4539 0.0343 -1.000 0.4219 0.01055 0.00338 -0.0842 0.4502 0.0352 -0.750 0.4452 0.01045 0.00324 -0.0832 0.4466 0.0362 -0.500 0.4693 0.01031 0.00310 -0.0824 0.4438 0.0370 -0.250 0.4929 0.01021 0.00298 -0.0815 0.4409 0.0376 0.000 0.5164 0.01016 0.00289 -0.0806 0.4379 0.0382 0.250 0.5384 0.01004 0.00273 -0.0793 0.4351 0.0390 0.500 0.5601 0.00994 0.00260 -0.0780 0.4320 0.0408 0.750 0.5842 0.00987 0.00254 -0.0772 0.4303 0.0426 1.000 0.6083 0.00984 0.00251 -0.0765 0.4283 0.0449 1.250 0.6324 0.00983 0.00251 -0.0757 0.4262 0.0467 1.500 0.6553 0.00977 0.00245 -0.0746 0.4239 0.0529 1.750 0.6777 0.00975 0.00245 -0.0735 0.4214 0.0687 2.000 0.6915 0.00929 0.00258 -0.0708 0.4191 0.3224 2.250 0.6784 0.00823 0.00268 -0.0622 0.4172 0.7582 2.500 1.0110 0.00898 0.00370 -0.1301 0.4109 1.0000 2.750 1.0337 0.00906 0.00375 -0.1292 0.4084 1.0000 3.000 1.0558 0.00916 0.00383 -0.1281 0.4061 1.0000 3.250 1.0769 0.00931 0.00393 -0.1269 0.4024 1.0000 3.500 1.0993 0.00940 0.00402 -0.1259 0.4005 1.0000 3.750 1.1222 0.00945 0.00409 -0.1250 0.3988 1.0000 4.000 1.1448 0.00953 0.00417 -0.1241 0.3971 1.0000 4.250 1.1671 0.00961 0.00426 -0.1231 0.3953 1.0000 4.500 1.1891 0.00970 0.00436 -0.1221 0.3936 1.0000 4.750 1.2106 0.00981 0.00447 -0.1209 0.3918 1.0000 5.000 1.2315 0.00994 0.00459 -0.1197 0.3899 1.0000 5.250 1.2517 0.01011 0.00474 -0.1183 0.3875 1.0000 5.500 1.2725 0.01025 0.00490 -0.1171 0.3857 1.0000 5.750 1.2943 0.01028 0.00497 -0.1160 0.3834 1.0000 6.000 1.3156 0.01034 0.00505 -0.1149 0.3805 1.0000 6.250 1.3358 0.01043 0.00516 -0.1135 0.3773 1.0000 6.500 1.3546 0.01057 0.00529 -0.1119 0.3743 1.0000 6.750 1.3720 0.01077 0.00548 -0.1100 0.3711 1.0000 7.000 1.3927 0.01081 0.00558 -0.1088 0.3690 1.0000 7.250 1.4126 0.01087 0.00568 -0.1074 0.3653 1.0000 7.500 1.4291 0.01098 0.00580 -0.1053 0.3608 1.0000 7.750 1.4407 0.01114 0.00595 -0.1022 0.3569 1.0000 8.000 1.4574 0.01120 0.00605 -0.1001 0.3526 1.0000 8.250 1.4717 0.01130 0.00618 -0.0976 0.3467 1.0000 8.500 1.4838 0.01149 0.00635 -0.0947 0.3409 1.0000 8.750 1.4989 0.01161 0.00651 -0.0924 0.3330 1.0000 9.000 1.5102 0.01185 0.00672 -0.0894 0.3220 1.0000 9.250 1.5162 0.01226 0.00703 -0.0855 0.3014 1.0000 9.500 1.5117 0.01303 0.00763 -0.0797 0.2706 1.0000 9.750 1.5020 0.01404 0.00845 -0.0732 0.2385 1.0000 10.000 1.4884 0.01529 0.00951 -0.0664 0.2064 1.0000 10.250 1.4715 0.01682 0.01084 -0.0596 0.1729 1.0000 10.500 1.4395 0.01931 0.01307 -0.0515 0.1252 1.0000 10.750 1.4101 0.02223 0.01584 -0.0450 0.0887 1.0000 11.000 1.3749 0.02622 0.01967 -0.0395 0.0466 1.0000 11.250 1.3575 0.02948 0.02289 -0.0365 0.0253 1.0000 11.500 1.3519 0.03204 0.02548 -0.0347 0.0195 1.0000 11.750 1.3525 0.03418 0.02767 -0.0335 0.0183 1.0000 12.000 1.3504 0.03665 0.03020 -0.0323 0.0172 1.0000 12.250 1.3469 0.03932 0.03295 -0.0312 0.0160 1.0000 12.500 1.3458 0.04182 0.03553 -0.0303 0.0156 1.0000 12.750 1.3442 0.04444 0.03822 -0.0295 0.0151 1.0000 13.000 1.3415 0.04719 0.04105 -0.0287 0.0146 1.0000 13.250 1.3374 0.05017 0.04411 -0.0281 0.0142 1.0000 13.500 1.3304 0.05354 0.04755 -0.0274 0.0135 1.0000 13.750 1.3265 0.05664 0.05072 -0.0270 0.0134 1.0000 14.000 1.3180 0.06030 0.05447 -0.0266 0.0129 1.0000 14.250 1.3063 0.06447 0.05873 -0.0262 0.0126 1.0000 14.500 1.3064 0.06727 0.06160 -0.0261 0.0122 1.0000 14.750 1.3012 0.07074 0.06515 -0.0260 0.0121 1.0000 15.000 1.2993 0.07383 0.06831 -0.0259 0.0118 1.0000 15.250 1.2953 0.07724 0.07179 -0.0259 0.0115 1.0000 15.500 1.2900 0.08088 0.07550 -0.0260 0.0113 1.0000 15.750 1.2868 0.08423 0.07892 -0.0262 0.0110 1.0000 16.000 1.2802 0.08808 0.08284 -0.0264 0.0109 1.0000 16.250 1.2778 0.09142 0.08623 -0.0267 0.0106 1.0000 16.500 1.2709 0.09540 0.09028 -0.0270 0.0103 1.0000 16.750 1.2668 0.09905 0.09400 -0.0275 0.0103 1.0000 17.000 1.2526 0.10411 0.09914 -0.0281 0.0099 1.0000