XFOIL Version 6.94 Calculated polar for: MH 200 12.97% 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 0.2930 0.01196 0.00694 -0.0673 0.7999 0.8218 0.500 0.3505 0.01194 0.00684 -0.0674 0.7904 0.8319 1.000 0.4056 0.01203 0.00688 -0.0674 0.7785 0.8412 1.500 0.4535 0.01179 0.00671 -0.0655 0.7689 0.8510 2.000 0.5065 0.01154 0.00648 -0.0645 0.7549 0.8610 2.500 0.5647 0.01135 0.00626 -0.0647 0.7412 0.8696 3.000 0.6195 0.01134 0.00631 -0.0646 0.7270 0.8754 3.500 0.6700 0.01087 0.00595 -0.0633 0.7094 0.8848 4.000 0.7251 0.01065 0.00572 -0.0628 0.6877 0.8919 4.500 0.7746 0.01040 0.00560 -0.0615 0.6603 0.9002 5.000 0.8254 0.01031 0.00554 -0.0604 0.6197 0.9084 5.500 0.8654 0.01046 0.00540 -0.0570 0.5457 0.9193 6.000 0.8977 0.01113 0.00575 -0.0527 0.4597 0.9315 6.500 0.9270 0.01210 0.00638 -0.0483 0.3719 0.9456 7.500 0.9994 0.01447 0.00826 -0.0439 0.2290 1.0000 8.000 1.0388 0.01583 0.00943 -0.0429 0.1752 1.0000 8.500 1.0746 0.01737 0.01077 -0.0412 0.1306 1.0000 9.000 1.1023 0.01934 0.01249 -0.0384 0.0876 1.0000 9.500 1.1248 0.02166 0.01473 -0.0349 0.0600 1.0000 10.000 1.1490 0.02390 0.01703 -0.0319 0.0469 1.0000 11.500 1.1945 0.03358 0.02728 -0.0218 0.0252 1.0000 12.000 1.2070 0.03771 0.03187 -0.0188 0.0225 1.0000 12.500 1.2256 0.04055 0.03493 -0.0172 0.0193 1.0000 13.000 1.2323 0.04499 0.03962 -0.0153 0.0163 1.0000 13.500 1.2306 0.05045 0.04532 -0.0139 0.0140 1.0000 14.000 1.2075 0.05925 0.05458 -0.0126 0.0123 1.0000 14.500 1.1625 0.07182 0.06777 -0.0138 0.0115 1.0000 15.000 1.1199 0.08575 0.08222 -0.0189 0.0113 1.0000 15.500 1.0860 0.09987 0.09672 -0.0264 0.0113 1.0000 16.000 1.0552 0.11495 0.11211 -0.0360 0.0113 1.0000 16.500 1.0285 0.13054 0.12796 -0.0464 0.0115 1.0000 17.000 1.0067 0.14568 0.14329 -0.0567 0.0120 1.0000 18.500 0.8997 0.22623 0.22370 -0.0930 0.0181 1.0000 19.000 0.9041 0.23947 0.23694 -0.0983 0.0188 1.0000