HT22 (ht22-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT22 (ht22-il) Reynolds number: 50,000 Max Cl/Cd: 27.25 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht22-il-50000-n5.txt Download as CSV file: xf-ht22-il-50000-n5.csv |
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
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Polar data table (+)
Polar graphs
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