HAWKER TEMPEST 61% SEMISPAN AIRFOIL (tempest2-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: HAWKER TEMPEST 61% SEMISPAN AIRFOIL (tempest2-il) Reynolds number: 100,000 Max Cl/Cd: 49.91 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tempest2-il-100000.txt Download as CSV file: xf-tempest2-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HAWKER TEMPEST 61% 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5886 0.05879 0.05394 -0.0551 1.0000 0.0745
-9.500 -0.6807 0.06684 0.06170 -0.0474 1.0000 0.0739
-9.250 -0.7425 0.06114 0.05543 -0.0396 1.0000 0.0632
-9.000 -0.7514 0.05751 0.05168 -0.0360 1.0000 0.0628
-8.750 -0.7568 0.05398 0.04805 -0.0326 1.0000 0.0617
-8.500 -0.7655 0.05091 0.04475 -0.0282 1.0000 0.0613
-8.250 -0.7722 0.04782 0.04139 -0.0238 1.0000 0.0610
-8.000 -0.7762 0.04472 0.03798 -0.0195 1.0000 0.0604
-7.750 -0.7778 0.04158 0.03447 -0.0152 1.0000 0.0597
-7.500 -0.7759 0.03864 0.03114 -0.0112 1.0000 0.0592
-7.250 -0.7702 0.03593 0.02801 -0.0075 1.0000 0.0594
-7.000 -0.7607 0.03350 0.02518 -0.0043 1.0000 0.0600
-6.750 -0.7485 0.03157 0.02284 -0.0014 1.0000 0.0618
-6.500 -0.7342 0.02956 0.02050 0.0011 1.0000 0.0651
-6.250 -0.7172 0.02799 0.01889 0.0028 1.0000 0.0691
-6.000 -0.6984 0.02653 0.01723 0.0047 1.0000 0.0734
-5.750 -0.6798 0.02505 0.01569 0.0064 1.0000 0.0800
-5.500 -0.6629 0.02409 0.01461 0.0085 1.0000 0.0902
-5.250 -0.6465 0.02291 0.01349 0.0105 1.0000 0.1038
-5.000 -0.6329 0.02181 0.01259 0.0128 1.0000 0.1255
-4.750 -0.6200 0.02076 0.01164 0.0154 1.0000 0.1597
-4.500 -0.6084 0.01978 0.01096 0.0180 1.0000 0.1980
-4.250 -0.5963 0.01894 0.01039 0.0205 1.0000 0.2423
-4.000 -0.5858 0.01799 0.00990 0.0232 1.0000 0.3071
-3.750 -0.5807 0.01676 0.00961 0.0271 1.0000 0.4425
-3.500 -0.5745 0.01596 0.00977 0.0319 1.0000 0.6274
-3.250 -0.5556 0.01598 0.01020 0.0350 1.0000 0.7514
-3.000 -0.5260 0.01649 0.01077 0.0360 1.0000 0.8278
-2.750 -0.4856 0.01731 0.01146 0.0347 1.0000 0.8786
-2.500 -0.4316 0.01840 0.01230 0.0306 1.0000 0.9132
-2.250 -0.3584 0.01961 0.01322 0.0226 1.0000 0.9346
-2.000 -0.2929 0.02054 0.01389 0.0154 1.0000 0.9551
-1.750 -0.1993 0.02144 0.01451 0.0029 1.0000 0.9743
-1.500 -0.1064 0.02189 0.01475 -0.0102 1.0000 0.9941
-1.250 -0.0776 0.02182 0.01459 -0.0127 1.0000 1.0000
-1.000 -0.0464 0.02181 0.01449 -0.0155 0.9942 1.0000
-0.750 0.0000 0.02178 0.01438 -0.0208 0.9848 1.0000
-0.500 0.0427 0.02175 0.01428 -0.0252 0.9748 1.0000
-0.250 0.0855 0.02175 0.01423 -0.0294 0.9654 1.0000
0.000 0.1308 0.02173 0.01418 -0.0340 0.9565 1.0000
0.250 0.1671 0.02166 0.01410 -0.0367 0.9452 1.0000
0.500 0.2062 0.02161 0.01404 -0.0398 0.9349 1.0000
0.750 0.2552 0.02148 0.01393 -0.0446 0.9272 1.0000
1.000 0.2895 0.02137 0.01385 -0.0465 0.9153 1.0000
1.250 0.3281 0.02122 0.01374 -0.0491 0.9044 1.0000
1.500 0.3863 0.02082 0.01342 -0.0550 0.8981 1.0000
1.750 0.4268 0.02051 0.01319 -0.0576 0.8863 1.0000
2.000 0.4686 0.02012 0.01288 -0.0602 0.8750 1.0000
2.250 0.5162 0.01954 0.01242 -0.0636 0.8650 1.0000
2.500 0.5595 0.01895 0.01193 -0.0660 0.8539 1.0000
2.750 0.5913 0.01853 0.01163 -0.0662 0.8395 1.0000
3.000 0.6227 0.01806 0.01124 -0.0661 0.8243 1.0000
3.250 0.6442 0.01778 0.01103 -0.0642 0.8050 1.0000
3.500 0.6691 0.01738 0.01070 -0.0627 0.7854 1.0000
3.750 0.6963 0.01695 0.01035 -0.0616 0.7662 1.0000
4.000 0.7149 0.01680 0.01026 -0.0591 0.7439 1.0000
4.250 0.7390 0.01650 0.01000 -0.0575 0.7215 1.0000
4.500 0.7565 0.01638 0.00994 -0.0547 0.6951 1.0000
4.750 0.7747 0.01626 0.00986 -0.0521 0.6659 1.0000
5.000 0.7916 0.01618 0.00976 -0.0492 0.6316 1.0000
5.250 0.8057 0.01620 0.00972 -0.0458 0.5905 1.0000
5.500 0.8165 0.01636 0.00977 -0.0419 0.5408 1.0000
5.750 0.8244 0.01667 0.00991 -0.0376 0.4805 1.0000
6.000 0.8288 0.01723 0.01014 -0.0329 0.4073 1.0000
6.250 0.8291 0.01815 0.01058 -0.0277 0.3283 1.0000
6.500 0.8271 0.01934 0.01127 -0.0225 0.2541 1.0000
6.750 0.8246 0.02072 0.01217 -0.0173 0.1898 1.0000
7.000 0.8223 0.02225 0.01326 -0.0121 0.1428 1.0000
7.250 0.8246 0.02370 0.01445 -0.0077 0.1152 1.0000
7.500 0.8311 0.02516 0.01571 -0.0041 0.0974 1.0000
7.750 0.8449 0.02677 0.01717 -0.0018 0.0851 1.0000
8.000 0.8607 0.02796 0.01848 0.0004 0.0760 1.0000
8.250 0.8843 0.02993 0.02048 0.0011 0.0690 1.0000
8.500 0.9076 0.03176 0.02243 0.0020 0.0644 1.0000
8.750 0.9338 0.03455 0.02520 0.0018 0.0599 1.0000
9.000 0.9471 0.03626 0.02730 0.0045 0.0570 1.0000
9.250 0.9615 0.03876 0.03016 0.0068 0.0556 1.0000
9.500 0.9711 0.04145 0.03325 0.0096 0.0547 1.0000
9.750 0.9758 0.04419 0.03634 0.0130 0.0542 1.0000
10.000 0.9767 0.04686 0.03935 0.0166 0.0538 1.0000
10.250 0.9738 0.04958 0.04238 0.0205 0.0532 1.0000
10.500 0.9776 0.05181 0.04470 0.0231 0.0515 1.0000
10.750 0.9584 0.05494 0.04826 0.0286 0.0524 1.0000
11.000 0.9454 0.05745 0.05095 0.0331 0.0519 1.0000
11.250 0.9127 0.06094 0.05479 0.0386 0.0535 1.0000
11.500 0.8881 0.06446 0.05854 0.0418 0.0541 1.0000
11.750 0.8609 0.06864 0.06293 0.0436 0.0550 1.0000
12.000 0.8352 0.07348 0.06793 0.0439 0.0565 1.0000
12.250 0.8079 0.07875 0.07334 0.0428 0.0569 1.0000
12.500 0.7840 0.08481 0.07949 0.0406 0.0581 1.0000
12.750 0.7656 0.09117 0.08588 0.0380 0.0592 1.0000
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