XFOIL Version 6.94 Calculated polar for: FX 78-PK-188/20 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.500 0.1852 0.02689 0.02150 -0.0383 0.7223 0.7954 1.500 0.1947 0.02964 0.02423 -0.0282 0.6978 0.8076 2.000 0.2612 0.02916 0.02374 -0.0300 0.6959 0.8108 2.500 0.3227 0.02914 0.02372 -0.0314 0.6940 0.8139 3.000 0.3839 0.02929 0.02389 -0.0328 0.6905 0.8172 5.000 0.5286 0.03175 0.02647 -0.0286 0.6474 0.8312 5.500 0.5852 0.03130 0.02618 -0.0291 0.6411 0.8343 6.000 0.6628 0.02933 0.02433 -0.0316 0.6376 0.8365 6.500 0.7468 0.02683 0.02195 -0.0346 0.6357 0.8390 7.000 0.8568 0.02176 0.01702 -0.0397 0.6348 0.8408 7.500 0.9673 0.01778 0.01321 -0.0459 0.6305 0.8426 9.000 1.0597 0.01894 0.01421 -0.0374 0.4890 0.8542 9.500 1.0457 0.02195 0.01679 -0.0293 0.4009 0.8604 10.000 1.0174 0.02641 0.02070 -0.0212 0.3074 0.8662 11.500 1.0055 0.03825 0.03135 -0.0082 0.0981 0.8812 12.000 1.0200 0.04129 0.03437 -0.0060 0.0784 0.8881 12.500 1.0369 0.04432 0.03741 -0.0043 0.0669 0.8941 13.000 1.0649 0.04638 0.03950 -0.0034 0.0417 0.9029 13.500 1.0812 0.04953 0.04265 -0.0021 0.0315 0.9137 14.000 1.0997 0.05272 0.04600 -0.0012 0.0281 0.9283 14.500 1.0957 0.05876 0.05225 0.0004 0.0155 0.9691 15.000 1.1140 0.06268 0.05622 0.0000 0.0118 1.0000 15.500 1.1218 0.06782 0.06157 0.0000 0.0111 1.0000 16.000 1.1324 0.07276 0.06677 -0.0001 0.0119 1.0000 16.500 1.1399 0.07780 0.07198 -0.0002 0.0116 1.0000 17.000 1.1169 0.08624 0.08085 0.0016 0.0096 1.0000 17.500 1.1294 0.09132 0.08613 0.0001 0.0103 1.0000 18.000 1.1048 0.10179 0.09712 -0.0018 0.0084 1.0000 18.500 1.0900 0.11124 0.10692 -0.0050 0.0087 1.0000 19.000 1.0688 0.12219 0.11823 -0.0099 0.0090 1.0000 19.500 1.0326 0.13713 0.13360 -0.0179 0.0085 1.0000 20.000 0.9934 0.15326 0.15011 -0.0280 0.0090 1.0000