HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL (tempest3-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL (tempest3-il) Reynolds number: 100,000 Max Cl/Cd: 49.41 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tempest3-il-100000.txt Download as CSV file: xf-tempest3-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5323 0.09139 0.08656 -0.0304 1.0000 0.1261
-9.000 -0.5276 0.08825 0.08341 -0.0298 1.0000 0.1308
-8.750 -0.5532 0.08364 0.07895 -0.0344 1.0000 0.1348
-8.500 -0.5822 0.08011 0.07548 -0.0350 1.0000 0.1355
-8.250 -0.6136 0.07708 0.07239 -0.0347 1.0000 0.1363
-6.750 -0.6583 0.04521 0.03876 -0.0200 1.0000 0.0707
-6.500 -0.6487 0.04163 0.03499 -0.0173 1.0000 0.0658
-6.250 -0.6443 0.03740 0.03027 -0.0135 1.0000 0.0608
-6.000 -0.6346 0.03503 0.02696 -0.0090 1.0000 0.0565
-5.750 -0.6214 0.03182 0.02341 -0.0065 1.0000 0.0561
-5.500 -0.6056 0.02936 0.02055 -0.0041 1.0000 0.0562
-5.250 -0.5874 0.02690 0.01772 -0.0021 1.0000 0.0572
-5.000 -0.5691 0.02510 0.01592 -0.0007 1.0000 0.0620
-4.750 -0.5487 0.02373 0.01433 0.0011 1.0000 0.0668
-4.500 -0.5271 0.02204 0.01252 0.0027 1.0000 0.0710
-4.250 -0.5080 0.02096 0.01143 0.0044 1.0000 0.0809
-4.000 -0.4908 0.01976 0.01034 0.0064 1.0000 0.0974
-3.750 -0.4761 0.01847 0.00927 0.0088 1.0000 0.1351
-3.500 -0.4654 0.01682 0.00833 0.0117 1.0000 0.2288
-3.250 -0.4589 0.01509 0.00790 0.0152 1.0000 0.4384
-3.000 -0.4411 0.01413 0.00848 0.0194 1.0000 0.7822
-2.750 -0.3603 0.01543 0.00962 0.0128 1.0000 0.9242
-2.500 -0.2567 0.01650 0.01013 -0.0003 1.0000 0.9597
-2.250 -0.1628 0.01686 0.01005 -0.0128 1.0000 0.9836
-2.000 -0.0788 0.01668 0.00957 -0.0245 1.0000 1.0000
-1.750 -0.0841 0.01655 0.00939 -0.0201 1.0000 1.0000
-1.500 -0.0887 0.01648 0.00926 -0.0157 1.0000 1.0000
-1.250 -0.0919 0.01645 0.00915 -0.0115 1.0000 1.0000
-1.000 -0.0931 0.01648 0.00911 -0.0076 1.0000 1.0000
-0.750 -0.0921 0.01656 0.00912 -0.0040 1.0000 1.0000
-0.500 -0.0887 0.01669 0.00918 -0.0008 1.0000 1.0000
-0.250 -0.0470 0.01706 0.00946 -0.0048 0.9931 1.0000
0.000 0.0008 0.01743 0.00975 -0.0098 0.9840 1.0000
0.250 0.0450 0.01772 0.00999 -0.0140 0.9740 1.0000
0.500 0.0900 0.01800 0.01025 -0.0183 0.9644 1.0000
0.750 0.1389 0.01825 0.01049 -0.0232 0.9556 1.0000
1.000 0.1791 0.01839 0.01065 -0.0263 0.9441 1.0000
1.250 0.2208 0.01851 0.01080 -0.0295 0.9329 1.0000
1.500 0.2665 0.01858 0.01093 -0.0334 0.9227 1.0000
1.750 0.3205 0.01851 0.01095 -0.0387 0.9139 1.0000
2.000 0.3652 0.01838 0.01093 -0.0420 0.9018 1.0000
2.250 0.4150 0.01813 0.01084 -0.0461 0.8901 1.0000
2.500 0.4629 0.01776 0.01062 -0.0495 0.8779 1.0000
2.750 0.5068 0.01735 0.01037 -0.0520 0.8646 1.0000
3.000 0.5465 0.01690 0.01011 -0.0535 0.8494 1.0000
3.250 0.5853 0.01627 0.00963 -0.0542 0.8315 1.0000
3.500 0.6134 0.01582 0.00932 -0.0530 0.8091 1.0000
3.750 0.6431 0.01536 0.00899 -0.0519 0.7866 1.0000
4.000 0.6657 0.01507 0.00879 -0.0496 0.7593 1.0000
4.250 0.6844 0.01485 0.00864 -0.0465 0.7249 1.0000
4.500 0.7023 0.01460 0.00837 -0.0431 0.6795 1.0000
4.750 0.7177 0.01454 0.00819 -0.0394 0.6203 1.0000
5.000 0.7298 0.01477 0.00824 -0.0354 0.5461 1.0000
5.250 0.7354 0.01544 0.00837 -0.0304 0.4234 1.0000
5.500 0.7278 0.01740 0.00906 -0.0241 0.2258 1.0000
5.750 0.7228 0.01990 0.01052 -0.0185 0.1176 1.0000
6.000 0.7301 0.02149 0.01189 -0.0147 0.0914 1.0000
6.250 0.7416 0.02313 0.01335 -0.0118 0.0772 1.0000
6.500 0.7596 0.02435 0.01465 -0.0097 0.0678 1.0000
6.750 0.7836 0.02658 0.01683 -0.0087 0.0627 1.0000
7.000 0.8079 0.02840 0.01889 -0.0076 0.0582 1.0000
7.250 0.8297 0.03054 0.02101 -0.0068 0.0532 1.0000
7.500 0.8523 0.03379 0.02454 -0.0056 0.0517 1.0000
7.750 0.8695 0.03654 0.02769 -0.0035 0.0514 1.0000
8.000 0.8835 0.03988 0.03141 -0.0011 0.0516 1.0000
8.250 0.8956 0.04404 0.03592 0.0012 0.0522 1.0000
8.500 0.9045 0.04660 0.03885 0.0042 0.0526 1.0000
8.750 0.9080 0.05033 0.04294 0.0073 0.0524 1.0000
9.000 0.9111 0.05285 0.04584 0.0107 0.0529 1.0000
9.250 0.8841 0.05717 0.05111 0.0178 0.0603 1.0000
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Polar data table (+)
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