XFOIL Version 6.94 Calculated polar for: E222 (10.17%) 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 ------- -------- --------- --------- -------- ------- ------- 0.000 0.3628 0.00762 0.00302 -0.0870 0.8483 0.8556 0.500 0.4098 0.00754 0.00292 -0.0840 0.8213 0.9057 1.000 0.4626 0.00746 0.00280 -0.0823 0.7916 0.9579 1.500 0.5427 0.00746 0.00267 -0.0873 0.7588 1.0000 2.000 0.5919 0.00767 0.00270 -0.0860 0.7236 1.0000 2.500 0.6435 0.00794 0.00280 -0.0850 0.6865 1.0000 3.000 0.6947 0.00825 0.00299 -0.0840 0.6455 1.0000 3.500 0.7453 0.00863 0.00322 -0.0828 0.6021 1.0000 4.000 0.7949 0.00908 0.00354 -0.0814 0.5541 1.0000 4.500 0.8435 0.00961 0.00391 -0.0799 0.5021 1.0000 5.000 0.8911 0.01023 0.00440 -0.0783 0.4461 1.0000 5.500 0.9367 0.01100 0.00496 -0.0765 0.3811 1.0000 6.000 0.9788 0.01206 0.00565 -0.0742 0.2969 1.0000 6.500 1.0209 0.01324 0.00654 -0.0721 0.2214 1.0000 7.000 1.0609 0.01466 0.00759 -0.0698 0.1467 1.0000 7.500 1.1001 0.01617 0.00881 -0.0675 0.0878 1.0000 8.000 1.1268 0.01891 0.01115 -0.0630 0.0239 1.0000 8.500 1.1583 0.02092 0.01331 -0.0592 0.0175 1.0000 9.000 1.1842 0.02303 0.01566 -0.0545 0.0157 1.0000 9.500 1.2035 0.02537 0.01821 -0.0491 0.0147 1.0000 10.000 1.2206 0.02810 0.02113 -0.0439 0.0138 1.0000 10.500 1.2364 0.03135 0.02464 -0.0393 0.0133 1.0000 11.000 1.2522 0.03529 0.02886 -0.0352 0.0129 1.0000 11.500 1.2651 0.04001 0.03395 -0.0316 0.0128 1.0000 12.000 1.2689 0.04559 0.04004 -0.0280 0.0130 1.0000 12.500 1.2558 0.05310 0.04816 -0.0250 0.0135 1.0000 13.000 1.2213 0.06328 0.05900 -0.0243 0.0141 1.0000 13.500 1.1798 0.07548 0.07172 -0.0278 0.0145 1.0000 14.000 1.1354 0.09028 0.08696 -0.0354 0.0149 1.0000 14.500 1.0895 0.10841 0.10545 -0.0470 0.0152 1.0000 15.000 1.0373 0.13211 0.12945 -0.0630 0.0155 1.0000 15.500 0.9759 0.16364 0.16106 -0.0813 0.0168 1.0000 17.500 0.7639 0.20915 0.20703 -0.1033 0.0305 1.0000 18.000 0.7726 0.21712 0.21501 -0.1071 0.0278 1.0000 18.500 0.7896 0.22285 0.22078 -0.1086 0.0252 1.0000 19.000 0.7988 0.23408 0.23200 -0.1117 0.0241 1.0000 19.500 0.8046 0.24262 0.24055 -0.1162 0.0238 1.0000 20.000 0.8061 0.25154 0.24948 -0.1223 0.0210 1.0000 20.500 0.8152 0.25983 0.25779 -0.1259 0.0202 1.0000 21.000 0.8249 0.26792 0.26592 -0.1293 0.0188 1.0000 21.500 0.8372 0.27532 0.27334 -0.1317 0.0177 1.0000 22.000 0.8505 0.28614 0.28417 -0.1338 0.0171 1.0000 22.500 0.8542 0.29508 0.29312 -0.1385 0.0169 1.0000 23.000 0.8580 0.30429 0.30235 -0.1437 0.0160 1.0000 23.500 0.8660 0.31355 0.31163 -0.1473 0.0147 1.0000 24.000 0.8743 0.32261 0.32071 -0.1508 0.0138 1.0000 24.500 0.8827 0.33083 0.32898 -0.1539 0.0127 1.0000 25.000 0.8955 0.34043 0.33862 -0.1555 0.0120 1.0000 25.500 0.9005 0.35055 0.34874 -0.1594 0.0119 1.0000 26.000 0.9041 0.36022 0.35842 -0.1638 0.0118 1.0000