XFOIL Version 6.96 Calculated polar for: GOE 223 (MVA H.34) 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.000 -0.7580 0.10450 0.10197 -0.0697 1.0000 0.0114 -18.750 -0.7762 0.09765 0.09501 -0.0737 1.0000 0.0115 -18.500 -0.7892 0.09162 0.08886 -0.0777 0.9880 0.0116 -18.250 -0.7980 0.08627 0.08340 -0.0813 0.9784 0.0117 -18.000 -0.8057 0.08153 0.07856 -0.0840 0.9692 0.0118 -17.750 -0.8134 0.07725 0.07417 -0.0861 0.9599 0.0119 -17.500 -0.8198 0.07315 0.06998 -0.0881 0.9516 0.0121 -17.250 -0.8232 0.06965 0.06640 -0.0897 0.9431 0.0123 -17.000 -0.8243 0.06627 0.06295 -0.0914 0.9349 0.0124 -16.750 -0.8247 0.06308 0.05968 -0.0930 0.9269 0.0126 -16.500 -0.8222 0.06024 0.05677 -0.0944 0.9176 0.0128 -16.250 -0.8200 0.05739 0.05385 -0.0959 0.9075 0.0130 -16.000 -0.8165 0.05479 0.05115 -0.0972 0.8951 0.0132 -15.750 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0.01205 0.00552 -0.1488 0.5688 0.0254 -6.000 0.0380 0.01198 0.00532 -0.1491 0.5483 0.0257 -5.750 0.0666 0.01185 0.00509 -0.1495 0.5353 0.0260 -5.500 0.0956 0.01170 0.00488 -0.1499 0.5271 0.0262 -5.250 0.1245 0.01155 0.00466 -0.1504 0.5183 0.0264 -5.000 0.1536 0.01131 0.00433 -0.1510 0.5101 0.0269 -4.750 0.1826 0.01115 0.00411 -0.1514 0.5021 0.0274 -4.500 0.2117 0.01103 0.00394 -0.1519 0.4963 0.0279 -4.250 0.2412 0.01090 0.00378 -0.1523 0.4922 0.0285 -4.000 0.2705 0.01080 0.00364 -0.1528 0.4878 0.0291 -3.750 0.2996 0.01073 0.00353 -0.1532 0.4830 0.0296 -3.500 0.3288 0.01066 0.00342 -0.1535 0.4785 0.0301 -3.250 0.3583 0.01058 0.00331 -0.1540 0.4744 0.0306 -3.000 0.3875 0.01053 0.00322 -0.1543 0.4697 0.0311 -2.750 0.4164 0.01051 0.00316 -0.1547 0.4648 0.0316 -2.500 0.4456 0.01046 0.00308 -0.1550 0.4608 0.0327 -2.250 0.4750 0.01041 0.00301 -0.1554 0.4572 0.0341 -2.000 0.5041 0.01038 0.00296 -0.1558 0.4529 0.0358 -1.750 0.5329 0.01036 0.00292 -0.1561 0.4483 0.0408 -1.500 0.5624 0.01011 0.00282 -0.1568 0.4445 0.1071 -1.250 0.5929 0.00938 0.00257 -0.1581 0.4409 0.2804 -1.000 0.6219 0.00930 0.00259 -0.1586 0.4363 0.3208 -0.750 0.6505 0.00934 0.00264 -0.1588 0.4311 0.3361 -0.500 0.6791 0.00940 0.00269 -0.1591 0.4266 0.3461 -0.250 0.7077 0.00945 0.00274 -0.1593 0.4210 0.3555 0.000 0.7357 0.00955 0.00280 -0.1595 0.4138 0.3623 0.250 0.7637 0.00964 0.00288 -0.1596 0.4056 0.3707 0.500 0.7904 0.00983 0.00298 -0.1596 0.3900 0.3768 0.750 0.8149 0.01015 0.00316 -0.1592 0.3628 0.3820 1.000 0.8248 0.01146 0.00390 -0.1564 0.2550 0.3858 1.250 0.8463 0.01197 0.00424 -0.1556 0.2232 0.3911 1.500 0.8712 0.01223 0.00445 -0.1552 0.2123 0.3969 1.750 0.8967 0.01243 0.00462 -0.1550 0.2049 0.4015 2.000 0.9223 0.01262 0.00479 -0.1547 0.1999 0.4041 2.250 0.9472 0.01285 0.00498 -0.1544 0.1945 0.4067 2.500 0.9724 0.01304 0.00515 -0.1541 0.1901 0.4093 3.000 1.0217 0.01346 0.00553 -0.1533 0.1805 0.4149 3.250 1.0450 0.01371 0.00575 -0.1528 0.1745 0.4179 3.500 1.0635 0.01410 0.00606 -0.1513 0.1566 0.4208 3.750 1.0726 0.01490 0.00667 -0.1484 0.1155 0.4233 4.000 1.0939 0.01524 0.00700 -0.1475 0.1119 0.4262 4.250 1.1153 0.01559 0.00733 -0.1467 0.1088 0.4289 4.500 1.1368 0.01592 0.00768 -0.1459 0.1061 0.4329 4.750 1.1585 0.01624 0.00802 -0.1452 0.1046 0.4367 5.000 1.1800 0.01657 0.00837 -0.1445 0.1040 0.4404 5.250 1.2012 0.01692 0.00874 -0.1437 0.1035 0.4438 5.750 1.2424 0.01770 0.00956 -0.1421 0.1024 0.4511 6.000 1.2625 0.01812 0.01002 -0.1413 0.1020 0.4556 6.250 1.2823 0.01856 0.01049 -0.1404 0.1016 0.4603 6.500 1.3014 0.01905 0.01100 -0.1395 0.1010 0.4647 6.750 1.3194 0.01962 0.01160 -0.1385 0.0997 0.4703 7.000 1.3367 0.02024 0.01225 -0.1374 0.0983 0.4757 7.250 1.3540 0.02087 0.01290 -0.1364 0.0973 0.4807 7.500 1.3708 0.02154 0.01362 -0.1354 0.0961 0.4861 7.750 1.3877 0.02223 0.01435 -0.1344 0.0952 0.4923 8.000 1.4036 0.02300 0.01516 -0.1333 0.0941 0.4983 8.250 1.4193 0.02379 0.01600 -0.1323 0.0930 0.5049 8.500 1.4367 0.02448 0.01675 -0.1315 0.0928 0.5129 8.750 1.4542 0.02518 0.01750 -0.1308 0.0922 0.5216 9.000 1.4709 0.02595 0.01833 -0.1300 0.0914 0.5320 9.250 1.4868 0.02677 0.01922 -0.1291 0.0902 0.5430 9.500 1.5016 0.02770 0.02020 -0.1282 0.0887 0.5544 9.750 1.5150 0.02874 0.02129 -0.1272 0.0867 0.5673 10.000 1.5262 0.02997 0.02256 -0.1260 0.0838 0.5811 10.250 1.5387 0.03111 0.02376 -0.1250 0.0813 0.5961 10.500 1.5324 0.03378 0.02627 -0.1226 0.0519 0.6080 10.750 1.5099 0.03806 0.03050 -0.1192 0.0185 0.6172 11.000 1.5135 0.04017 0.03267 -0.1178 0.0143 0.6311 11.250 1.5205 0.04202 0.03460 -0.1169 0.0130 0.6455 11.500 1.5268 0.04400 0.03665 -0.1159 0.0122 0.6597 11.750 1.5327 0.04605 0.03878 -0.1150 0.0115 0.6733 12.000 1.5380 0.04820 0.04101 -0.1141 0.0108 0.6867 12.250 1.5438 0.05034 0.04324 -0.1134 0.0105 0.7007 12.500 1.5491 0.05257 0.04558 -0.1127 0.0101 0.7176 12.750 1.5541 0.05489 0.04802 -0.1121 0.0096 0.7456 13.000 1.5561 0.05693 0.05049 -0.1110 0.0092 1.0000 13.250 1.5582 0.05962 0.05324 -0.1104 0.0088 1.0000 13.500 1.5592 0.06246 0.05614 -0.1098 0.0085 1.0000 13.750 1.5621 0.06514 0.05888 -0.1093 0.0083 1.0000 14.000 1.5649 0.06785 0.06165 -0.1089 0.0081 1.0000 14.250 1.5667 0.07071 0.06457 -0.1086 0.0079 1.0000 14.500 1.5680 0.07361 0.06753 -0.1082 0.0077 1.0000 14.750 1.5694 0.07651 0.07049 -0.1079 0.0074 1.0000 15.000 1.5698 0.07956 0.07360 -0.1077 0.0072 1.0000 15.250 1.5700 0.08266 0.07676 -0.1075 0.0071 1.0000 15.500 1.5703 0.08575 0.07990 -0.1073 0.0069 1.0000 15.750 1.5691 0.08906 0.08328 -0.1072 0.0067 1.0000 16.000 1.5679 0.09231 0.08658 -0.1071 0.0065 1.0000