XFOIL Version 6.96 Calculated polar for: SG6042 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.250 -0.3181 0.08596 0.08244 -0.0538 0.9860 0.0188 -8.000 -0.3081 0.08228 0.07877 -0.0569 0.9813 0.0181 -7.500 -0.3045 0.06485 0.06136 -0.0770 0.9628 0.0153 -7.250 -0.2934 0.05804 0.05445 -0.0853 0.9551 0.0152 -7.000 -0.2784 0.05082 0.04705 -0.0929 0.9488 0.0150 -6.750 -0.2672 0.04308 0.03898 -0.0982 0.9415 0.0149 -6.500 -0.2533 0.03346 0.02861 -0.1030 0.9354 0.0150 -6.250 -0.2269 0.02861 0.02310 -0.1060 0.9330 0.0159 -6.000 -0.2061 0.02777 0.02218 -0.1056 0.9272 0.0166 -5.750 -0.1797 0.02503 0.01896 -0.1065 0.9235 0.0177 -5.500 -0.1496 0.02218 0.01554 -0.1077 0.9211 0.0182 -5.250 -0.1169 0.02015 0.01302 -0.1090 0.9194 0.0190 -5.000 -0.0857 0.01877 0.01142 -0.1100 0.9171 0.0198 -4.750 -0.0629 0.01819 0.01079 -0.1092 0.9111 0.0210 -4.500 -0.0322 0.01739 0.00984 -0.1098 0.9080 0.0228 -4.250 0.0002 0.01644 0.00873 -0.1107 0.9056 0.0238 -4.000 0.0335 0.01559 0.00785 -0.1120 0.9036 0.0252 -3.750 0.0575 0.01513 0.00736 -0.1113 0.8978 0.0269 -3.500 0.0870 0.01466 0.00681 -0.1116 0.8938 0.0298 -3.250 0.1193 0.01411 0.00626 -0.1126 0.8909 0.0336 -3.000 0.1532 0.01357 0.00568 -0.1138 0.8885 0.0398 -2.750 0.1771 0.01326 0.00540 -0.1130 0.8821 0.0509 -2.500 0.2074 0.01292 0.00508 -0.1135 0.8778 0.0700 -2.250 0.2404 0.01255 0.00477 -0.1146 0.8745 0.0959 -2.000 0.2672 0.01220 0.00461 -0.1146 0.8689 0.1429 -1.750 0.2950 0.01171 0.00443 -0.1148 0.8633 0.2306 -1.500 0.3256 0.01104 0.00425 -0.1157 0.8593 0.3875 -1.250 0.3492 0.01051 0.00432 -0.1149 0.8532 0.5685 -1.000 0.3749 0.01029 0.00433 -0.1141 0.8472 0.6655 -0.750 0.4047 0.01010 0.00424 -0.1140 0.8427 0.7262 -0.500 0.4260 0.01004 0.00427 -0.1123 0.8342 0.7697 -0.250 0.4526 0.00990 0.00418 -0.1114 0.8285 0.8175 0.000 0.4722 0.00981 0.00419 -0.1091 0.8204 0.8704 0.250 0.5025 0.00964 0.00406 -0.1089 0.8140 0.9329 0.500 0.5462 0.00954 0.00393 -0.1121 0.8057 1.0000 0.750 0.5762 0.00953 0.00381 -0.1124 0.7975 1.0000 1.000 0.6013 0.00958 0.00380 -0.1119 0.7866 1.0000 1.250 0.6288 0.00961 0.00377 -0.1117 0.7767 1.0000 1.500 0.6573 0.00964 0.00371 -0.1117 0.7664 1.0000 1.750 0.6831 0.00969 0.00372 -0.1112 0.7535 1.0000 2.000 0.7092 0.00974 0.00371 -0.1107 0.7396 1.0000 2.250 0.7355 0.00981 0.00371 -0.1103 0.7245 1.0000 2.500 0.7619 0.00988 0.00371 -0.1098 0.7074 1.0000 2.750 0.7874 0.00998 0.00374 -0.1092 0.6881 1.0000 3.000 0.8127 0.01011 0.00379 -0.1085 0.6673 1.0000 3.250 0.8376 0.01028 0.00384 -0.1078 0.6442 1.0000 3.500 0.8615 0.01048 0.00394 -0.1069 0.6174 1.0000 3.750 0.8842 0.01074 0.00406 -0.1057 0.5872 1.0000 4.000 0.9058 0.01106 0.00421 -0.1044 0.5546 1.0000 4.250 0.9267 0.01141 0.00441 -0.1030 0.5213 1.0000 4.500 0.9468 0.01181 0.00466 -0.1015 0.4874 1.0000 4.750 0.9661 0.01225 0.00494 -0.0999 0.4526 1.0000 5.250 1.0027 0.01325 0.00560 -0.0964 0.3823 1.0000 5.500 1.0205 0.01379 0.00599 -0.0947 0.3478 1.0000 5.750 1.0379 0.01436 0.00640 -0.0929 0.3142 1.0000 6.000 1.0557 0.01493 0.00683 -0.0913 0.2845 1.0000 6.250 1.0733 0.01551 0.00728 -0.0896 0.2562 1.0000 6.500 1.0910 0.01609 0.00776 -0.0880 0.2313 1.0000 6.750 1.1084 0.01666 0.00824 -0.0863 0.2093 1.0000 7.000 1.1251 0.01724 0.00874 -0.0846 0.1903 1.0000 7.250 1.1422 0.01781 0.00928 -0.0829 0.1732 1.0000 7.500 1.1590 0.01840 0.00983 -0.0812 0.1578 1.0000 7.750 1.1757 0.01901 0.01041 -0.0795 0.1449 1.0000 8.000 1.1920 0.01965 0.01102 -0.0777 0.1335 1.0000 8.250 1.2086 0.02028 0.01166 -0.0761 0.1227 1.0000 8.500 1.2250 0.02092 0.01232 -0.0745 0.1135 1.0000 8.750 1.2402 0.02164 0.01303 -0.0727 0.1055 1.0000 9.000 1.2560 0.02233 0.01376 -0.0710 0.0978 1.0000 9.250 1.2706 0.02310 0.01455 -0.0693 0.0913 1.0000 9.500 1.2854 0.02386 0.01536 -0.0676 0.0849 1.0000 9.750 1.2990 0.02471 0.01624 -0.0658 0.0796 1.0000 10.000 1.3135 0.02551 0.01712 -0.0642 0.0741 1.0000 10.250 1.3248 0.02652 0.01812 -0.0623 0.0696 1.0000 10.500 1.3392 0.02736 0.01911 -0.0607 0.0654 1.0000 10.750 1.3514 0.02835 0.02015 -0.0591 0.0613 1.0000 11.000 1.3612 0.02953 0.02136 -0.0572 0.0581 1.0000 11.250 1.3739 0.03054 0.02250 -0.0557 0.0548 1.0000 11.500 1.3845 0.03170 0.02374 -0.0541 0.0515 1.0000 11.750 1.3914 0.03317 0.02524 -0.0522 0.0488 1.0000 12.000 1.4021 0.03440 0.02663 -0.0508 0.0463 1.0000 12.250 1.4114 0.03576 0.02811 -0.0493 0.0437 1.0000 12.500 1.4184 0.03732 0.02975 -0.0478 0.0415 1.0000 12.750 1.4220 0.03924 0.03171 -0.0462 0.0396 1.0000 13.000 1.4295 0.04088 0.03354 -0.0449 0.0379 1.0000 13.250 1.4356 0.04269 0.03549 -0.0437 0.0362 1.0000 13.500 1.4401 0.04467 0.03759 -0.0426 0.0346 1.0000 13.750 1.4424 0.04692 0.03994 -0.0416 0.0333 1.0000 14.000 1.4414 0.04959 0.04268 -0.0406 0.0321 1.0000 14.250 1.4449 0.05191 0.04519 -0.0399 0.0310 1.0000 14.500 1.4465 0.05452 0.04797 -0.0393 0.0299 1.0000 14.750 1.4467 0.05735 0.05096 -0.0389 0.0289 1.0000 15.000 1.4459 0.06041 0.05416 -0.0388 0.0281 1.0000 15.250 1.4439 0.06373 0.05762 -0.0389 0.0274 1.0000 15.500 1.4405 0.06736 0.06137 -0.0393 0.0268 1.0000 15.750 1.4355 0.07135 0.06547 -0.0400 0.0262 1.0000 16.000 1.4293 0.07563 0.06987 -0.0408 0.0257 1.0000 16.250 1.4248 0.07989 0.07435 -0.0419 0.0253 1.0000 16.500 1.4190 0.08450 0.07916 -0.0433 0.0248 1.0000 16.750 1.4119 0.08946 0.08432 -0.0451 0.0243 1.0000 17.000 1.4038 0.09475 0.08980 -0.0472 0.0238 1.0000 17.250 1.3948 0.10033 0.09555 -0.0497 0.0234 1.0000 17.500 1.3851 0.10624 0.10164 -0.0526 0.0230 1.0000 17.750 1.3747 0.11243 0.10799 -0.0558 0.0227 1.0000 18.000 1.3638 0.11887 0.11460 -0.0593 0.0224 1.0000 18.250 1.3522 0.12558 0.12147 -0.0632 0.0221 1.0000 18.500 1.3400 0.13261 0.12865 -0.0674 0.0219 1.0000 18.750 1.3275 0.13990 0.13609 -0.0719 0.0217 1.0000 19.000 1.3142 0.14754 0.14387 -0.0767 0.0215 1.0000