XFOIL Version 6.96 Calculated polar for: Dormoy 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.3223 0.08389 0.08185 -0.0293 1.0000 0.0091 -10.250 -0.3225 0.08019 0.07818 -0.0300 1.0000 0.0094 -10.000 -0.3238 0.07637 0.07438 -0.0307 1.0000 0.0097 -9.750 -0.3264 0.07241 0.07045 -0.0316 1.0000 0.0098 -9.500 -0.3299 0.06851 0.06657 -0.0324 1.0000 0.0099 -9.250 -0.3347 0.06471 0.06281 -0.0331 1.0000 0.0104 -9.000 -0.3422 0.06090 0.05904 -0.0339 1.0000 0.0107 -8.750 -0.3550 0.05734 0.05554 -0.0343 1.0000 0.0102 -8.500 -0.3743 0.05425 0.05251 -0.0342 1.0000 0.0099 -8.250 -0.3733 0.04861 0.04684 -0.0396 0.9972 0.0104 -8.000 -0.3573 0.04125 0.03936 -0.0478 0.9907 0.0108 -7.750 -0.3375 0.03449 0.03243 -0.0540 0.9840 0.0112 -7.500 -0.3145 0.02880 0.02651 -0.0581 0.9759 0.0127 -7.250 -0.2785 0.02630 0.02369 -0.0610 0.9693 0.0143 -7.000 -0.2545 0.02246 0.01952 -0.0631 0.9565 0.0144 -6.750 -0.2303 0.01884 0.01558 -0.0645 0.9424 0.0145 -6.500 -0.2076 0.01580 0.01220 -0.0650 0.9250 0.0145 -4.000 0.0234 0.01093 0.00452 -0.0600 0.8094 0.0178 -3.750 0.0481 0.01040 0.00392 -0.0592 0.7993 0.0208 -3.500 0.0729 0.00988 0.00329 -0.0583 0.7896 0.0204 -3.250 0.0981 0.00946 0.00275 -0.0575 0.7793 0.0201 -3.000 0.1236 0.00913 0.00230 -0.0568 0.7674 0.0213 -2.750 0.1490 0.00893 0.00193 -0.0560 0.7506 0.0241 -2.500 0.1746 0.00879 0.00165 -0.0553 0.7313 0.0326 -2.250 0.1975 0.00819 0.00150 -0.0545 0.7142 0.1923 -2.000 0.2174 0.00732 0.00140 -0.0534 0.6965 0.4464 -1.750 0.2305 0.00633 0.00140 -0.0504 0.6753 0.7487 -1.500 0.2831 0.00616 0.00153 -0.0550 0.6253 0.9629 -1.250 0.3262 0.00652 0.00152 -0.0583 0.5609 0.9832 -1.000 0.3658 0.00684 0.00152 -0.0611 0.5011 0.9920 -0.750 0.4051 0.00736 0.00157 -0.0641 0.4026 0.9993 -0.500 0.4271 0.00780 0.00167 -0.0633 0.3418 1.0000 -0.250 0.4487 0.00804 0.00174 -0.0623 0.3159 1.0000 0.000 0.4711 0.00823 0.00181 -0.0613 0.2953 1.0000 0.250 0.4934 0.00844 0.00188 -0.0604 0.2697 1.0000 0.500 0.5116 0.00905 0.00205 -0.0588 0.1784 1.0000 0.750 0.5332 0.00936 0.00223 -0.0578 0.1583 1.0000 1.000 0.5563 0.00954 0.00237 -0.0570 0.1488 1.0000 1.250 0.5795 0.00974 0.00251 -0.0562 0.1405 1.0000 1.500 0.6003 0.01016 0.00269 -0.0551 0.0825 1.0000 1.750 0.6216 0.01058 0.00302 -0.0540 0.0625 1.0000 2.000 0.6450 0.01079 0.00325 -0.0532 0.0586 1.0000 2.250 0.6684 0.01099 0.00351 -0.0525 0.0549 1.0000 2.500 0.6914 0.01125 0.00379 -0.0517 0.0504 1.0000 2.750 0.7150 0.01146 0.00400 -0.0510 0.0470 1.0000 3.000 0.7396 0.01157 0.00411 -0.0506 0.0440 1.0000 3.250 0.7630 0.01182 0.00426 -0.0498 0.0232 1.0000 3.500 0.7860 0.01215 0.00466 -0.0489 0.0163 1.0000 3.750 0.8088 0.01251 0.00513 -0.0480 0.0150 1.0000 4.000 0.8311 0.01295 0.00566 -0.0470 0.0143 1.0000 4.250 0.8516 0.01359 0.00642 -0.0457 0.0125 1.0000 4.500 0.8702 0.01442 0.00738 -0.0441 0.0114 1.0000 4.750 0.8854 0.01557 0.00869 -0.0418 0.0108 1.0000 5.000 0.8986 0.01687 0.01012 -0.0393 0.0106 1.0000 5.250 0.9141 0.01799 0.01136 -0.0372 0.0108 1.0000 5.500 0.9328 0.01884 0.01228 -0.0356 0.0114 1.0000 5.750 0.9524 0.02003 0.01364 -0.0337 0.0146 1.0000 8.000 1.0745 0.04730 0.04269 -0.0186 0.0102 1.0000 8.250 1.0739 0.05021 0.04585 -0.0157 0.0102 1.0000 8.500 1.0702 0.05303 0.04890 -0.0126 0.0101 1.0000 8.750 1.0624 0.05560 0.05169 -0.0092 0.0101 1.0000 9.000 1.0502 0.05801 0.05425 -0.0055 0.0101 1.0000 9.250 1.0368 0.05995 0.05636 -0.0021 0.0100 1.0000 9.500 1.0237 0.06255 0.05911 -0.0002 0.0099 1.0000 9.750 1.0298 0.06296 0.05964 0.0011 0.0090 1.0000 10.000 1.0153 0.06636 0.06319 0.0015 0.0089 1.0000 10.250 0.9994 0.07034 0.06731 0.0011 0.0088 1.0000 10.500 0.8592 0.07795 0.07524 -0.0020 0.0102 1.0000 10.750 0.8382 0.08423 0.08163 -0.0048 0.0102 1.0000