XFOIL Version 6.96 Calculated polar for: HT22 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.6736 0.13300 0.12604 0.0417 1.0001 0.0876 -9.500 -0.6788 0.13066 0.12377 0.0372 1.0001 0.0887 -9.250 -0.6827 0.12791 0.12109 0.0329 1.0001 0.0891 -9.000 -0.6576 0.12087 0.11397 0.0389 1.0001 0.0951 -8.750 -0.6554 0.11748 0.11063 0.0369 1.0001 0.0995 -8.500 -0.6621 0.11495 0.10820 0.0315 1.0001 0.1025 -8.250 -0.6677 0.11198 0.10535 0.0247 1.0001 0.1032 -8.000 -0.6460 0.10599 0.09931 0.0315 1.0001 0.1079 -7.750 -0.6415 0.10228 0.09564 0.0297 1.0001 0.1114 -7.500 -0.6459 0.09898 0.09240 0.0178 1.0001 0.1172 -7.000 -0.6248 0.08951 0.08300 0.0179 1.0001 0.1207 -6.750 -0.6139 0.08517 0.07865 0.0156 1.0001 0.1227 -6.500 -0.5896 0.07446 0.06762 0.0037 1.0001 0.0581 -6.000 -0.5517 0.06161 0.05415 -0.0071 1.0001 0.0480 -5.750 -0.5342 0.05712 0.04954 -0.0086 1.0001 0.0471 -5.500 -0.5139 0.05251 0.04466 -0.0106 1.0001 0.0466 -5.250 -0.4907 0.04791 0.03961 -0.0126 1.0001 0.0472 -5.000 -0.4654 0.04371 0.03478 -0.0142 1.0001 0.0483 -4.750 -0.4410 0.03982 0.03046 -0.0150 1.0001 0.0490 -4.500 -0.4154 0.03631 0.02648 -0.0154 1.0001 0.0493 -4.250 -0.3893 0.03320 0.02297 -0.0156 1.0001 0.0501 -4.000 -0.3632 0.03077 0.02028 -0.0156 1.0001 0.0525 -3.750 -0.3358 0.02867 0.01779 -0.0155 1.0001 0.0571 -3.500 -0.3072 0.02649 0.01511 -0.0150 1.0001 0.0601 -3.250 -0.2796 0.02448 0.01281 -0.0145 1.0001 0.0634 -3.000 -0.2527 0.02307 0.01129 -0.0140 1.0001 0.0715 -2.750 -0.2252 0.02156 0.00962 -0.0133 1.0001 0.0778 -2.500 -0.1981 0.02043 0.00836 -0.0127 1.0001 0.0904 -2.250 -0.1711 0.01928 0.00718 -0.0122 1.0001 0.1055 -2.000 -0.1442 0.01816 0.00617 -0.0119 1.0001 0.1372 -1.750 -0.1184 0.01637 0.00525 -0.0119 1.0001 0.2686 -1.500 -0.0847 0.01362 0.00469 -0.0110 1.0001 0.9999 -1.250 -0.0583 0.01356 0.00426 -0.0105 1.0001 0.9999 -1.000 -0.0320 0.01353 0.00392 -0.0101 1.0001 0.9999 -0.750 -0.0057 0.01350 0.00368 -0.0098 1.0001 0.9999 -0.500 0.0205 0.01349 0.00351 -0.0094 1.0001 0.9999 -0.250 0.0467 0.01349 0.00337 -0.0091 1.0001 0.9999 0.000 0.0728 0.01351 0.00330 -0.0087 1.0001 0.9999 0.250 0.0988 0.01353 0.00328 -0.0084 1.0001 0.9999 0.500 0.1248 0.01357 0.00332 -0.0081 1.0001 0.9999 0.750 0.1505 0.01363 0.00340 -0.0078 1.0001 0.9999 1.000 0.1761 0.01371 0.00354 -0.0075 1.0001 0.9999 1.250 0.2015 0.01381 0.00374 -0.0073 1.0001 0.9999 1.500 0.2354 0.01397 0.00405 -0.0089 0.9740 0.9999 1.750 0.2896 0.01427 0.00439 -0.0136 0.8561 0.9999 2.000 0.3223 0.01471 0.00458 -0.0130 0.7457 0.9999 2.250 0.3451 0.01526 0.00478 -0.0108 0.6628 0.9999 2.500 0.3679 0.01585 0.00504 -0.0090 0.5970 0.9999 2.750 0.3917 0.01643 0.00540 -0.0077 0.5412 0.9999 3.000 0.4162 0.01701 0.00577 -0.0066 0.4920 0.9999 3.250 0.4412 0.01757 0.00619 -0.0058 0.4453 0.9999 3.500 0.4663 0.01815 0.00664 -0.0051 0.4000 0.9999 3.750 0.4916 0.01873 0.00716 -0.0045 0.3545 0.9999 4.000 0.5169 0.01935 0.00767 -0.0040 0.3085 0.9999 4.250 0.5422 0.02003 0.00822 -0.0036 0.2631 0.9999 4.500 0.5678 0.02084 0.00891 -0.0033 0.2199 0.9999 4.750 0.5938 0.02181 0.00985 -0.0031 0.1827 0.9999 5.000 0.6192 0.02291 0.01089 -0.0028 0.1544 0.9999 5.250 0.6444 0.02412 0.01208 -0.0025 0.1336 0.9999 5.500 0.6695 0.02541 0.01345 -0.0021 0.1171 0.9999 5.750 0.6943 0.02691 0.01507 -0.0015 0.1064 0.9999 6.000 0.7184 0.02832 0.01650 -0.0012 0.0959 0.9999 6.250 0.7435 0.03013 0.01870 -0.0007 0.0882 0.9999 6.500 0.7672 0.03205 0.02065 -0.0003 0.0834 0.9999 6.750 0.7912 0.03445 0.02364 0.0000 0.0773 0.9999 7.000 0.8136 0.03637 0.02578 0.0002 0.0719 0.9999 7.250 0.8348 0.03945 0.02923 0.0004 0.0694 0.9999 7.500 0.8534 0.04363 0.03417 0.0002 0.0674 0.9999 7.750 0.8683 0.04823 0.03945 -0.0005 0.0649 0.9999 8.000 0.8815 0.05225 0.04391 -0.0013 0.0619 0.9999 8.250 0.8964 0.05497 0.04675 -0.0015 0.0591 0.9999 8.500 0.9055 0.05941 0.05140 -0.0023 0.0579 0.9999 8.750 0.9039 0.06593 0.05840 -0.0051 0.0577 0.9999 9.000 0.8976 0.07271 0.06548 -0.0088 0.0577 0.9999 9.250 0.8886 0.07963 0.07257 -0.0133 0.0579 0.9999