XFOIL Version 6.96 Calculated polar for: MH 120 11.57% 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.3756 0.11500 0.10807 -0.0246 1.0000 0.2551 -9.500 -0.3776 0.11230 0.10545 -0.0243 1.0000 0.2666 -9.250 -0.3912 0.11121 0.10447 -0.0244 1.0000 0.2773 -9.000 -0.3776 0.10726 0.10054 -0.0232 1.0000 0.2905 -8.750 -0.3728 0.10399 0.09733 -0.0222 1.0000 0.3042 -8.500 -0.3641 0.10050 0.09389 -0.0213 1.0000 0.3145 -8.250 -0.3638 0.09765 0.09112 -0.0203 1.0000 0.3265 -8.000 -0.3660 0.09511 0.08867 -0.0191 1.0000 0.3391 -7.750 -0.3697 0.09266 0.08632 -0.0177 1.0000 0.3523 -7.250 -0.3820 0.08833 0.08222 -0.0137 1.0000 0.3796 -7.000 -0.3903 0.08633 0.08035 -0.0111 1.0000 0.3936 -6.750 -0.3716 0.08199 0.07602 -0.0103 1.0000 0.3993 -5.500 -0.5420 0.05631 0.04987 -0.0225 1.0000 0.1615 -5.250 -0.5374 0.05167 0.04487 -0.0211 1.0000 0.1432 -5.000 -0.5321 0.04781 0.04046 -0.0192 1.0000 0.1305 -4.750 -0.5250 0.04436 0.03615 -0.0165 1.0000 0.1200 -4.500 -0.5124 0.04161 0.03320 -0.0146 1.0000 0.1164 -4.250 -0.4988 0.03899 0.03008 -0.0123 1.0000 0.1122 -4.000 -0.4834 0.03691 0.02728 -0.0099 1.0000 0.1086 -3.750 -0.4662 0.03534 0.02521 -0.0078 1.0000 0.1074 -3.500 -0.4485 0.03350 0.02324 -0.0064 1.0000 0.1097 -3.250 -0.4305 0.03216 0.02176 -0.0049 1.0000 0.1147 -3.000 -0.4106 0.03097 0.02027 -0.0034 1.0000 0.1173 -2.750 -0.3893 0.02992 0.01897 -0.0020 1.0000 0.1200 -2.500 -0.3670 0.02875 0.01783 -0.0011 1.0000 0.1262 -2.250 -0.3446 0.02806 0.01696 -0.0001 1.0000 0.1345 -2.000 -0.1946 0.02351 0.01607 -0.0188 1.0000 1.0000 -1.750 -0.1852 0.02375 0.01589 -0.0170 1.0000 1.0000 -1.500 -0.1742 0.02407 0.01582 -0.0154 1.0000 1.0000 -1.250 -0.1622 0.02445 0.01586 -0.0139 1.0000 1.0000 -1.000 -0.1494 0.02487 0.01598 -0.0126 1.0000 1.0000 -0.750 -0.1360 0.02535 0.01616 -0.0114 1.0000 1.0000 -0.500 -0.1078 0.02613 0.01661 -0.0132 0.9954 1.0000 -0.250 -0.0634 0.02718 0.01734 -0.0180 0.9840 1.0000 0.000 -0.0221 0.02818 0.01804 -0.0221 0.9730 1.0000 0.250 0.0151 0.02905 0.01869 -0.0254 0.9615 1.0000 0.500 0.0479 0.02986 0.01930 -0.0277 0.9502 1.0000 0.750 0.0805 0.03070 0.01996 -0.0300 0.9390 1.0000 1.000 0.1146 0.03160 0.02072 -0.0324 0.9281 1.0000 1.250 0.1531 0.03257 0.02155 -0.0355 0.9173 1.0000 1.500 0.1786 0.03334 0.02223 -0.0364 0.9058 1.0000 1.750 0.2041 0.03417 0.02297 -0.0372 0.8945 1.0000 2.000 0.2324 0.03505 0.02379 -0.0384 0.8833 1.0000 2.250 0.2646 0.03596 0.02466 -0.0402 0.8721 1.0000 2.500 0.2981 0.03686 0.02553 -0.0422 0.8609 1.0000 2.750 0.3190 0.03772 0.02637 -0.0421 0.8487 1.0000 3.000 0.3413 0.03865 0.02728 -0.0422 0.8366 1.0000 3.250 0.3663 0.03957 0.02822 -0.0426 0.8244 1.0000 3.500 0.3929 0.04049 0.02918 -0.0433 0.8118 1.0000 3.750 0.4206 0.04139 0.03011 -0.0440 0.7990 1.0000 4.000 0.4484 0.04227 0.03104 -0.0446 0.7856 1.0000 4.250 0.4763 0.04312 0.03196 -0.0451 0.7721 1.0000 4.500 0.5028 0.04397 0.03291 -0.0454 0.7579 1.0000 4.750 0.5280 0.04481 0.03384 -0.0454 0.7433 1.0000 5.000 0.5517 0.04568 0.03480 -0.0451 0.7282 1.0000 5.250 0.5750 0.04654 0.03577 -0.0447 0.7125 1.0000 5.500 0.5993 0.04734 0.03673 -0.0443 0.6966 1.0000 5.750 0.6274 0.04794 0.03748 -0.0441 0.6800 1.0000 6.000 0.6608 0.04823 0.03796 -0.0441 0.6635 1.0000 6.250 0.7061 0.04774 0.03775 -0.0448 0.6469 1.0000 6.500 0.7206 0.04868 0.03882 -0.0429 0.6282 1.0000 6.750 0.7471 0.04883 0.03918 -0.0416 0.6089 1.0000 7.000 0.8192 0.04580 0.03662 -0.0429 0.5910 1.0000 7.250 0.8558 0.04487 0.03597 -0.0418 0.5699 1.0000 7.500 0.9513 0.03952 0.03115 -0.0444 0.5446 1.0000 7.750 0.9996 0.03733 0.02928 -0.0436 0.5155 1.0000 8.000 1.0324 0.03612 0.02826 -0.0416 0.4838 1.0000 8.250 1.0757 0.03424 0.02643 -0.0404 0.4452 1.0000 8.500 1.0915 0.03414 0.02637 -0.0368 0.4092 1.0000 8.750 1.1077 0.03400 0.02617 -0.0332 0.3696 1.0000 9.000 1.1158 0.03421 0.02618 -0.0288 0.3289 1.0000 9.250 1.1139 0.03482 0.02650 -0.0234 0.2881 1.0000 9.500 1.1029 0.03588 0.02730 -0.0175 0.2515 1.0000 9.750 1.0867 0.03729 0.02842 -0.0112 0.2179 1.0000 10.000 1.0682 0.03907 0.02998 -0.0053 0.1875 1.0000 10.250 1.0516 0.04143 0.03205 -0.0004 0.1559 1.0000 10.500 1.0460 0.04433 0.03445 0.0030 0.1246 1.0000 10.750 1.0585 0.04741 0.03753 0.0051 0.1020 1.0000 11.000 1.0859 0.05060 0.04053 0.0054 0.0863 1.0000 11.250 1.0952 0.05376 0.04416 0.0073 0.0811 1.0000 11.500 1.1111 0.05721 0.04783 0.0084 0.0763 1.0000 11.750 1.1332 0.06202 0.05281 0.0083 0.0733 1.0000 12.000 1.1268 0.06553 0.05668 0.0108 0.0731 1.0000 12.250 1.1146 0.06923 0.06072 0.0132 0.0729 1.0000 12.500 1.0987 0.07316 0.06494 0.0152 0.0729 1.0000 12.750 1.0814 0.07746 0.06949 0.0164 0.0730 1.0000 13.000 1.0618 0.08205 0.07431 0.0168 0.0731 1.0000 13.250 1.0468 0.08687 0.07934 0.0167 0.0736 1.0000 13.500 0.9688 0.09581 0.08870 0.0112 0.0775 1.0000 13.750 0.9246 0.10607 0.09910 0.0050 0.0811 1.0000