XFOIL Version 6.96 Calculated polar for: GOE 255 (MVA CA.6) 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 ------ -------- --------- --------- -------- -------- -------- -19.500 -0.6547 0.13828 0.13592 -0.0476 1.0000 0.0099 -19.250 -0.6688 0.13132 0.12887 -0.0515 1.0000 0.0099 -19.000 -0.6796 0.12516 0.12263 -0.0549 1.0000 0.0100 -18.750 -0.6894 0.11933 0.11672 -0.0581 1.0000 0.0100 -18.500 -0.6996 0.11355 0.11086 -0.0613 1.0000 0.0100 -18.250 -0.7086 0.10805 0.10529 -0.0643 1.0000 0.0101 -18.000 -0.7164 0.10287 0.10004 -0.0671 1.0000 0.0101 -17.750 -0.7249 0.09767 0.09476 -0.0699 1.0000 0.0102 -17.500 -0.7331 0.09254 0.08957 -0.0727 1.0000 0.0102 -17.250 -0.7407 0.08759 0.08454 -0.0754 1.0000 0.0103 -17.000 -0.7480 0.08280 0.07968 -0.0780 1.0000 0.0103 -16.750 -0.7550 0.07812 0.07493 -0.0806 1.0000 0.0104 -16.500 -0.7619 0.07359 0.07032 -0.0831 1.0000 0.0105 -16.250 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0.01027 0.00411 -0.1084 0.6980 0.0860 -6.750 -0.2128 0.00998 0.00387 -0.1086 0.6936 0.0990 -6.500 -0.1848 0.00970 0.00365 -0.1088 0.6886 0.1180 -6.250 -0.1568 0.00946 0.00346 -0.1090 0.6836 0.1388 -6.000 -0.1280 0.00925 0.00331 -0.1093 0.6786 0.1558 -5.750 -0.0992 0.00909 0.00316 -0.1096 0.6722 0.1698 -5.500 -0.0706 0.00897 0.00303 -0.1098 0.6657 0.1832 -5.250 -0.0415 0.00883 0.00291 -0.1102 0.6587 0.1957 -5.000 -0.0130 0.00871 0.00278 -0.1104 0.6507 0.2090 -4.750 0.0159 0.00855 0.00265 -0.1107 0.6424 0.2247 -4.500 0.0441 0.00841 0.00252 -0.1109 0.6338 0.2437 -4.250 0.0727 0.00821 0.00240 -0.1112 0.6250 0.2707 -4.000 0.1010 0.00809 0.00234 -0.1114 0.6155 0.3045 -3.750 0.1297 0.00806 0.00232 -0.1116 0.6046 0.3261 -3.500 0.1587 0.00808 0.00231 -0.1119 0.5941 0.3401 -3.250 0.1875 0.00813 0.00231 -0.1121 0.5844 0.3517 -3.000 0.2165 0.00816 0.00231 -0.1123 0.5760 0.3602 -2.750 0.2454 0.00823 0.00232 -0.1126 0.5686 0.3666 -2.500 0.2746 0.00828 0.00232 -0.1129 0.5622 0.3720 -2.250 0.3033 0.00833 0.00235 -0.1131 0.5567 0.3793 -2.000 0.3326 0.00840 0.00237 -0.1134 0.5523 0.3846 -1.750 0.3619 0.00844 0.00238 -0.1137 0.5483 0.3875 -1.500 0.3907 0.00845 0.00237 -0.1140 0.5442 0.3918 -1.250 0.4194 0.00850 0.00240 -0.1142 0.5401 0.3953 -1.000 0.4484 0.00855 0.00242 -0.1145 0.5367 0.3990 -0.750 0.4778 0.00858 0.00244 -0.1149 0.5339 0.4022 -0.500 0.5070 0.00863 0.00246 -0.1152 0.5311 0.4045 -0.250 0.5357 0.00864 0.00247 -0.1155 0.5281 0.4082 0.000 0.5641 0.00869 0.00251 -0.1157 0.5248 0.4114 0.250 0.5926 0.00876 0.00256 -0.1159 0.5217 0.4154 0.500 0.6219 0.00879 0.00260 -0.1163 0.5198 0.4189 0.750 0.6510 0.00882 0.00263 -0.1166 0.5175 0.4220 1.000 0.6798 0.00882 0.00266 -0.1169 0.5151 0.4267 1.250 0.7084 0.00886 0.00271 -0.1172 0.5125 0.4305 1.500 0.7367 0.00893 0.00277 -0.1174 0.5097 0.4346 1.750 0.7646 0.00903 0.00285 -0.1176 0.5065 0.4388 2.000 0.7933 0.00903 0.00290 -0.1179 0.5041 0.4443 2.250 0.8221 0.00905 0.00295 -0.1182 0.5014 0.4486 2.500 0.8506 0.00908 0.00300 -0.1184 0.4982 0.4527 2.750 0.8784 0.00915 0.00307 -0.1186 0.4940 0.4572 3.000 0.9053 0.00924 0.00316 -0.1186 0.4891 0.4635 3.250 0.9341 0.00924 0.00322 -0.1189 0.4857 0.4705 3.500 0.9622 0.00926 0.00329 -0.1191 0.4818 0.4802 3.750 0.9895 0.00931 0.00338 -0.1192 0.4774 0.4941 4.000 1.0161 0.00937 0.00350 -0.1192 0.4729 0.5176 4.250 1.0443 0.00931 0.00359 -0.1195 0.4684 0.5599 4.500 1.0710 0.00926 0.00372 -0.1195 0.4618 0.6238 4.750 1.0967 0.00920 0.00387 -0.1194 0.4545 0.7046 5.000 1.1204 0.00910 0.00403 -0.1187 0.4429 0.8077 5.250 1.1435 0.00899 0.00421 -0.1177 0.4253 1.0000 5.500 1.1597 0.00954 0.00452 -0.1158 0.3774 1.0000 5.750 1.1721 0.01026 0.00500 -0.1132 0.3417 1.0000 6.000 1.1895 0.01070 0.00536 -0.1116 0.3276 1.0000 6.250 1.2061 0.01110 0.00571 -0.1097 0.3177 1.0000 6.500 1.2251 0.01144 0.00601 -0.1083 0.3108 1.0000 6.750 1.2421 0.01187 0.00640 -0.1067 0.3031 1.0000 7.000 1.2640 0.01212 0.00667 -0.1059 0.2987 1.0000 7.250 1.2833 0.01249 0.00702 -0.1047 0.2929 1.0000 7.500 1.3007 0.01295 0.00745 -0.1032 0.2868 1.0000 7.750 1.3235 0.01319 0.00771 -0.1027 0.2834 1.0000 8.000 1.3436 0.01355 0.00807 -0.1017 0.2782 1.0000 8.250 1.3613 0.01402 0.00852 -0.1004 0.2728 1.0000 8.500 1.3821 0.01437 0.00888 -0.0996 0.2681 1.0000 8.750 1.4015 0.01478 0.00930 -0.0987 0.2617 1.0000 9.000 1.4178 0.01535 0.00984 -0.0973 0.2546 1.0000 9.250 1.4369 0.01580 0.01029 -0.0964 0.2466 1.0000 9.500 1.4516 0.01649 0.01093 -0.0949 0.2346 1.0000 9.750 1.4583 0.01762 0.01193 -0.0924 0.2109 1.0000 10.000 1.4514 0.01964 0.01372 -0.0885 0.1739 1.0000 10.250 1.4474 0.02167 0.01562 -0.0854 0.1517 1.0000 10.500 1.4476 0.02359 0.01746 -0.0830 0.1341 1.0000 10.750 1.4426 0.02598 0.01971 -0.0804 0.1104 1.0000 11.000 1.4263 0.02935 0.02287 -0.0771 0.0777 1.0000 11.250 1.4130 0.03263 0.02602 -0.0743 0.0530 1.0000 11.500 1.3900 0.03691 0.03017 -0.0711 0.0184 1.0000 11.750 1.3945 0.03892 0.03221 -0.0700 0.0154 1.0000 12.000 1.4014 0.04077 0.03411 -0.0691 0.0145 1.0000 12.250 1.4070 0.04276 0.03616 -0.0682 0.0137 1.0000 12.500 1.4111 0.04493 0.03839 -0.0673 0.0129 1.0000 12.750 1.4171 0.04696 0.04047 -0.0666 0.0124 1.0000 13.000 1.4231 0.04902 0.04259 -0.0659 0.0120 1.0000 13.250 1.4282 0.05119 0.04482 -0.0652 0.0116 1.0000 13.500 1.4319 0.05357 0.04725 -0.0646 0.0112 1.0000 13.750 1.4345 0.05609 0.04984 -0.0640 0.0109 1.0000 14.000 1.4346 0.05892 0.05274 -0.0634 0.0105 1.0000 14.250 1.4327 0.06201 0.05591 -0.0628 0.0102 1.0000 14.500 1.4364 0.06455 0.05851 -0.0625 0.0101 1.0000 14.750 1.4394 0.06717 0.06119 -0.0622 0.0099 1.0000 15.000 1.4414 0.06994 0.06404 -0.0620 0.0097 1.0000 15.250 1.4420 0.07290 0.06707 -0.0618 0.0095 1.0000 15.500 1.4423 0.07591 0.07014 -0.0616 0.0093 1.0000 15.750 1.4419 0.07903 0.07334 -0.0615 0.0091 1.0000 16.000 1.4403 0.08235 0.07672 -0.0615 0.0088 1.0000 16.250 1.4387 0.08570 0.08014 -0.0615 0.0087 1.0000 16.500 1.4339 0.08948 0.08400 -0.0616 0.0085 1.0000 16.750 1.4262 0.09367 0.08828 -0.0619 0.0083 1.0000 17.000 1.4146 0.09849 0.09321 -0.0622 0.0082 1.0000