XFOIL Version 6.96 Calculated polar for: GOE 703 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -18.250 -0.7644 0.10082 0.09523 -0.0696 1.0000 0.0381 -17.750 -0.8266 0.08382 0.07775 -0.0795 1.0000 0.0382 -17.500 -0.8376 0.07911 0.07293 -0.0817 1.0000 0.0383 -17.250 -0.8483 0.07458 0.06828 -0.0837 1.0000 0.0384 -17.000 -0.8565 0.07060 0.06420 -0.0852 1.0000 0.0386 -16.750 -0.8632 0.06698 0.06049 -0.0863 1.0000 0.0388 -16.500 -0.8686 0.06368 0.05710 -0.0871 1.0000 0.0389 -16.250 -0.8735 0.06060 0.05392 -0.0876 1.0000 0.0392 -16.000 -0.8783 0.05766 0.05088 -0.0878 1.0000 0.0394 -15.750 -0.8820 0.05502 0.04815 -0.0877 1.0000 0.0396 -15.500 -0.8849 0.05256 0.04558 -0.0872 1.0000 0.0398 -15.250 -0.8871 0.05030 0.04322 -0.0865 1.0000 0.0401 -15.000 -0.8885 0.04823 0.04106 -0.0855 1.0000 0.0404 -14.750 -0.8890 0.04632 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0.5794 0.8115 -0.250 0.2820 0.01472 0.00744 -0.0440 0.5743 0.8196 0.000 0.3012 0.01494 0.00762 -0.0419 0.5694 0.8315 0.250 0.3337 0.01535 0.00803 -0.0424 0.5636 0.8382 0.500 0.3502 0.01550 0.00815 -0.0398 0.5584 0.8487 0.750 0.3892 0.01593 0.00849 -0.0417 0.5535 0.8524 1.000 0.4171 0.01619 0.00874 -0.0414 0.5484 0.8589 1.250 0.4364 0.01634 0.00890 -0.0396 0.5430 0.8671 1.500 0.4759 0.01670 0.00921 -0.0416 0.5373 0.8705 1.750 0.5073 0.01697 0.00940 -0.0421 0.5325 0.8761 2.000 0.5203 0.01704 0.00951 -0.0391 0.5273 0.8843 2.250 0.5537 0.01720 0.00967 -0.0402 0.5214 0.8864 2.500 0.5838 0.01733 0.00974 -0.0407 0.5159 0.8889 2.750 0.6100 0.01744 0.00984 -0.0404 0.5106 0.8925 3.000 0.6136 0.01745 0.00987 -0.0356 0.5055 0.9010 3.250 0.6458 0.01757 0.00998 -0.0366 0.4998 0.9026 3.500 0.6761 0.01769 0.01004 -0.0372 0.4942 0.9045 3.750 0.7027 0.01780 0.01019 -0.0370 0.4866 0.9072 4.000 0.7251 0.01789 0.01026 -0.0360 0.4794 0.9109 4.250 0.7280 0.01795 0.01029 -0.0311 0.4740 0.9183 4.500 0.7571 0.01806 0.01043 -0.0316 0.4655 0.9200 4.750 0.7835 0.01817 0.01049 -0.0315 0.4577 0.9220 5.000 0.8081 0.01829 0.01064 -0.0310 0.4496 0.9246 5.250 0.8278 0.01842 0.01075 -0.0296 0.4415 0.9283 5.750 0.8548 0.01866 0.01099 -0.0243 0.4259 0.9368 6.000 0.8796 0.01882 0.01113 -0.0240 0.4170 0.9390 6.250 0.9000 0.01898 0.01129 -0.0228 0.4074 0.9418 6.500 0.9151 0.01915 0.01145 -0.0206 0.4004 0.9456 6.750 0.9180 0.01931 0.01164 -0.0159 0.3938 0.9516 7.000 0.9403 0.01948 0.01180 -0.0152 0.3863 0.9536 7.250 0.9603 0.01965 0.01200 -0.0141 0.3790 0.9560 7.500 0.9759 0.01987 0.01222 -0.0122 0.3715 0.9593 7.750 0.9837 0.02014 0.01248 -0.0087 0.3653 0.9644 8.000 0.9986 0.02038 0.01276 -0.0068 0.3575 0.9673 8.250 1.0164 0.02069 0.01304 -0.0057 0.3491 0.9696 8.500 1.0329 0.02102 0.01340 -0.0043 0.3389 0.9725 8.750 1.0445 0.02147 0.01383 -0.0021 0.3300 0.9764 9.000 1.0536 0.02194 0.01432 0.0005 0.3207 0.9802 9.250 1.0705 0.02243 0.01481 0.0013 0.3111 0.9822 9.500 1.0855 0.02299 0.01537 0.0024 0.3006 0.9847 9.750 1.1004 0.02362 0.01602 0.0034 0.2910 0.9877 10.000 1.1104 0.02445 0.01684 0.0049 0.2805 0.9910 10.250 1.1228 0.02525 0.01765 0.0060 0.2687 0.9933 10.500 1.1355 0.02614 0.01855 0.0068 0.2580 0.9957 10.750 1.1464 0.02724 0.01963 0.0075 0.2472 0.9982 11.000 1.1576 0.02836 0.02076 0.0082 0.2354 1.0000 11.250 1.1522 0.02953 0.02193 0.0119 0.2269 1.0000 11.500 1.1474 0.03076 0.02316 0.0154 0.2185 1.0000 11.750 1.1422 0.03209 0.02449 0.0187 0.2105 1.0000 12.000 1.1356 0.03361 0.02599 0.0219 0.2022 1.0000 12.250 1.1314 0.03507 0.02745 0.0247 0.1955 1.0000 12.500 1.1259 0.03670 0.02909 0.0275 0.1885 1.0000 12.750 1.1213 0.03837 0.03076 0.0300 0.1825 1.0000 13.000 1.1183 0.04002 0.03243 0.0322 0.1768 1.0000 13.250 1.1137 0.04188 0.03428 0.0344 0.1722 1.0000 13.500 1.1133 0.04348 0.03592 0.0362 0.1683 1.0000 13.750 1.1127 0.04516 0.03763 0.0379 0.1642 1.0000 14.000 1.1096 0.04713 0.03960 0.0396 0.1600 1.0000 14.250 1.1082 0.04901 0.04150 0.0410 0.1563 1.0000 14.500 1.1094 0.05074 0.04328 0.0423 0.1526 1.0000 14.750 1.1088 0.05268 0.04524 0.0436 0.1489 1.0000 15.000 1.1067 0.05479 0.04735 0.0447 0.1455 1.0000 15.250 1.1085 0.05661 0.04921 0.0457 0.1429 1.0000 15.500 1.1107 0.05845 0.05113 0.0466 0.1396 1.0000 15.750 1.1112 0.06050 0.05322 0.0474 0.1365 1.0000 16.000 1.1105 0.06270 0.05543 0.0481 0.1334 1.0000 16.250 1.1112 0.06483 0.05759 0.0487 0.1307 1.0000 16.500 1.1134 0.06687 0.05972 0.0492 0.1275 1.0000 16.750 1.1139 0.06913 0.06202 0.0496 0.1244 1.0000 17.000 1.1122 0.07166 0.06457 0.0499 0.1212 1.0000 17.250 1.1122 0.07405 0.06703 0.0502 0.1180 1.0000 17.500 1.1127 0.07648 0.06954 0.0503 0.1145 1.0000 17.750 1.1106 0.07923 0.07233 0.0503 0.1111 1.0000 18.000 1.1084 0.08203 0.07515 0.0503 0.1079 1.0000 18.250 1.1080 0.08470 0.07794 0.0501 0.1040 1.0000 18.500 1.1039 0.08786 0.08114 0.0498 0.1000 1.0000 18.750 1.1010 0.09094 0.08430 0.0494 0.0959 1.0000 19.000 1.0975 0.09414 0.08755 0.0489 0.0913 1.0000 19.250 1.0930 0.09751 0.09098 0.0483 0.0870 1.0000