XFOIL Version 6.96 Calculated polar for: NACA 65(3)-618 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 ------ -------- --------- --------- -------- -------- -------- -18.000 -0.7321 0.09190 0.08860 -0.0844 1.0000 0.0168 -17.750 -0.7633 0.08253 0.07903 -0.0899 1.0000 0.0168 -17.500 -0.7825 0.07582 0.07218 -0.0937 1.0000 0.0169 -17.250 -0.7940 0.07071 0.06697 -0.0964 1.0000 0.0170 -17.000 -0.8061 0.06577 0.06191 -0.0988 1.0000 0.0171 -16.750 -0.8121 0.06199 0.05805 -0.1005 1.0000 0.0172 -16.500 -0.8157 0.05874 0.05474 -0.1018 1.0000 0.0173 -16.250 -0.8215 0.05542 0.05133 -0.1027 1.0000 0.0174 -16.000 -0.8241 0.05272 0.04856 -0.1033 1.0000 0.0175 -15.750 -0.8200 0.05000 0.04578 -0.1046 0.9928 0.0177 -15.500 -0.8110 0.04706 0.04272 -0.1075 0.9834 0.0180 -15.250 -0.7990 0.04428 0.03982 -0.1107 0.9733 0.0182 -15.000 -0.7825 0.04169 0.03707 -0.1144 0.9648 0.0185 -14.750 -0.7612 0.03915 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0.0549 -4.250 0.0141 0.01136 0.00373 -0.1053 0.6806 0.0751 -4.000 0.0397 0.01094 0.00349 -0.1055 0.6775 0.1193 -3.750 0.0650 0.01038 0.00321 -0.1059 0.6741 0.1943 -3.500 0.0906 0.00967 0.00288 -0.1065 0.6708 0.3013 -3.250 0.1170 0.00887 0.00256 -0.1073 0.6676 0.4387 -3.000 0.1454 0.00864 0.00254 -0.1079 0.6648 0.5126 -2.750 0.1744 0.00858 0.00259 -0.1083 0.6622 0.5527 -2.500 0.2035 0.00861 0.00266 -0.1087 0.6594 0.5805 -2.250 0.2325 0.00867 0.00273 -0.1090 0.6565 0.5985 -2.000 0.2614 0.00872 0.00277 -0.1093 0.6537 0.6084 -1.750 0.2905 0.00877 0.00273 -0.1098 0.6510 0.6128 -1.500 0.3192 0.00879 0.00272 -0.1101 0.6483 0.6152 -1.250 0.3481 0.00879 0.00273 -0.1104 0.6458 0.6177 -1.000 0.3771 0.00880 0.00274 -0.1108 0.6432 0.6204 -0.750 0.4061 0.00882 0.00274 -0.1112 0.6406 0.6230 -0.500 0.4350 0.00885 0.00275 -0.1116 0.6381 0.6257 -0.250 0.4639 0.00890 0.00276 -0.1120 0.6356 0.6285 0.000 0.4928 0.00894 0.00276 -0.1124 0.6332 0.6310 0.250 0.5215 0.00898 0.00280 -0.1128 0.6308 0.6332 0.500 0.5501 0.00900 0.00285 -0.1131 0.6283 0.6356 0.750 0.5788 0.00904 0.00290 -0.1135 0.6260 0.6381 1.000 0.6074 0.00908 0.00296 -0.1138 0.6236 0.6410 1.250 0.6361 0.00913 0.00301 -0.1142 0.6211 0.6440 1.500 0.6647 0.00919 0.00306 -0.1145 0.6186 0.6468 1.750 0.6932 0.00926 0.00311 -0.1149 0.6162 0.6493 2.000 0.7217 0.00933 0.00320 -0.1152 0.6141 0.6517 2.250 0.7499 0.00937 0.00330 -0.1155 0.6119 0.6543 2.500 0.7781 0.00942 0.00340 -0.1158 0.6093 0.6572 2.750 0.8062 0.00948 0.00350 -0.1160 0.6067 0.6605 3.000 0.8343 0.00956 0.00359 -0.1163 0.6042 0.6639 3.250 0.8625 0.00964 0.00368 -0.1166 0.6017 0.6669 3.500 0.8903 0.00972 0.00379 -0.1168 0.5989 0.6696 3.750 0.9175 0.00979 0.00392 -0.1169 0.5953 0.6726 4.000 0.9441 0.00984 0.00404 -0.1168 0.5906 0.6759 4.250 0.9708 0.00992 0.00415 -0.1168 0.5861 0.6793 4.500 0.9975 0.01002 0.00425 -0.1168 0.5818 0.6829 4.750 1.0227 0.01008 0.00438 -0.1165 0.5749 0.6864 5.000 1.0464 0.01017 0.00448 -0.1159 0.5658 0.6900 5.250 1.0697 0.01025 0.00462 -0.1152 0.5552 0.6938 5.500 1.0915 0.01038 0.00476 -0.1142 0.5428 0.6978 5.750 1.1105 0.01056 0.00491 -0.1127 0.5242 0.7018 6.000 1.1253 0.01083 0.00511 -0.1104 0.5006 0.7055 6.250 1.1348 0.01116 0.00538 -0.1071 0.4720 0.7095 6.500 1.1327 0.01184 0.00587 -0.1018 0.4298 0.7143 6.750 1.1235 0.01295 0.00672 -0.0957 0.3785 0.7195 7.000 1.1172 0.01414 0.00770 -0.0904 0.3350 0.7244 7.250 1.1127 0.01539 0.00878 -0.0858 0.2944 0.7297 7.750 1.1078 0.01813 0.01119 -0.0781 0.2211 0.7406 8.000 1.1069 0.01957 0.01251 -0.0748 0.1882 0.7457 8.250 1.1073 0.02106 0.01387 -0.0719 0.1582 0.7515 8.500 1.1082 0.02261 0.01530 -0.0692 0.1297 0.7573 8.750 1.1097 0.02419 0.01677 -0.0667 0.1036 0.7629 9.000 1.1122 0.02577 0.01827 -0.0645 0.0813 0.7695 9.250 1.1163 0.02734 0.01975 -0.0626 0.0627 0.7761 9.500 1.1223 0.02879 0.02118 -0.0609 0.0485 0.7827 9.750 1.1300 0.03019 0.02257 -0.0594 0.0398 0.7899 10.000 1.1392 0.03152 0.02392 -0.0582 0.0344 0.7968 10.250 1.1493 0.03280 0.02523 -0.0571 0.0309 0.8041 10.500 1.1601 0.03408 0.02656 -0.0561 0.0285 0.8118 10.750 1.1704 0.03539 0.02793 -0.0551 0.0264 0.8196 11.000 1.1809 0.03674 0.02934 -0.0541 0.0248 0.8283 11.250 1.1916 0.03805 0.03073 -0.0532 0.0234 0.8378 11.500 1.2015 0.03945 0.03219 -0.0523 0.0222 0.8477 11.750 1.2100 0.04096 0.03377 -0.0513 0.0212 0.8589 12.000 1.2201 0.04231 0.03522 -0.0503 0.0203 0.8713 12.250 1.2288 0.04377 0.03677 -0.0493 0.0195 0.8862 12.500 1.2367 0.04523 0.03832 -0.0482 0.0189 0.9063 12.750 1.2439 0.04685 0.04003 -0.0472 0.0182 0.9369 13.250 1.2629 0.05025 0.04356 -0.0465 0.0171 1.0000 13.500 1.2724 0.05209 0.04545 -0.0463 0.0165 1.0000 13.750 1.2817 0.05394 0.04735 -0.0460 0.0160 1.0000 14.000 1.2898 0.05596 0.04942 -0.0458 0.0156 1.0000 14.250 1.2973 0.05806 0.05156 -0.0456 0.0153 1.0000 14.500 1.3028 0.06043 0.05397 -0.0454 0.0149 1.0000 14.750 1.3106 0.06258 0.05620 -0.0453 0.0146 1.0000 15.000 1.3177 0.06484 0.05853 -0.0453 0.0143 1.0000 15.250 1.3245 0.06716 0.06092 -0.0454 0.0140 1.0000 15.500 1.3311 0.06953 0.06336 -0.0455 0.0137 1.0000 15.750 1.3369 0.07205 0.06595 -0.0456 0.0134 1.0000 16.000 1.3429 0.07456 0.06853 -0.0458 0.0131 1.0000 16.250 1.3482 0.07721 0.07123 -0.0462 0.0128 1.0000 16.500 1.3526 0.08000 0.07409 -0.0465 0.0126 1.0000 16.750 1.3554 0.08304 0.07719 -0.0470 0.0125 1.0000 17.000 1.3567 0.08630 0.08053 -0.0475 0.0123 1.0000