HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL (tempest3-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL (tempest3-il) Reynolds number: 200,000 Max Cl/Cd: 65.17 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tempest3-il-200000.txt Download as CSV file: xf-tempest3-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.250 -0.6654 0.02982 0.02351 -0.0065 1.0000 0.0310
-6.000 -0.6546 0.02712 0.02042 -0.0034 1.0000 0.0304
-5.750 -0.6403 0.02485 0.01778 -0.0008 1.0000 0.0303
-5.500 -0.6237 0.02371 0.01635 0.0014 1.0000 0.0320
-5.250 -0.6061 0.02291 0.01528 0.0035 1.0000 0.0330
-5.000 -0.5865 0.02083 0.01296 0.0051 1.0000 0.0334
-4.750 -0.5679 0.01886 0.01089 0.0069 1.0000 0.0350
-4.500 -0.5507 0.01784 0.00985 0.0088 1.0000 0.0371
-4.250 -0.5241 0.01704 0.00899 0.0088 0.9980 0.0415
-4.000 -0.4898 0.01611 0.00805 0.0072 0.9939 0.0507
-3.750 -0.4582 0.01510 0.00713 0.0062 0.9887 0.0767
-3.500 -0.4262 0.01405 0.00663 0.0047 0.9840 0.1805
-3.250 -0.3985 0.01312 0.00634 0.0038 0.9782 0.3122
-3.000 -0.3769 0.01192 0.00626 0.0045 0.9718 0.5551
-2.750 -0.3517 0.01132 0.00647 0.0057 0.9668 0.7438
-2.500 -0.3159 0.01131 0.00668 0.0050 0.9622 0.8437
-2.250 -0.2675 0.01160 0.00692 0.0016 0.9600 0.8932
-2.000 -0.2152 0.01194 0.00712 -0.0030 0.9584 0.9199
-1.750 -0.1613 0.01228 0.00732 -0.0080 0.9571 0.9373
-1.500 -0.1015 0.01258 0.00750 -0.0142 0.9566 0.9474
-1.250 -0.0411 0.01285 0.00765 -0.0207 0.9562 0.9585
-1.000 0.0268 0.01310 0.00781 -0.0286 0.9571 0.9723
-0.750 0.0858 0.01308 0.00773 -0.0351 0.9561 0.9804
-0.500 0.1418 0.01289 0.00751 -0.0412 0.9539 0.9855
-0.250 0.1928 0.01265 0.00725 -0.0463 0.9488 0.9910
0.000 0.2465 0.01237 0.00697 -0.0520 0.9454 0.9948
0.250 0.3030 0.01199 0.00660 -0.0582 0.9426 0.9977
0.500 0.3485 0.01164 0.00629 -0.0621 0.9346 1.0000
0.750 0.3933 0.01125 0.00592 -0.0657 0.9270 1.0000
1.000 0.4271 0.01092 0.00562 -0.0670 0.9133 1.0000
1.250 0.4552 0.01068 0.00539 -0.0670 0.8973 1.0000
1.500 0.4796 0.01050 0.00524 -0.0662 0.8800 1.0000
1.750 0.5031 0.01037 0.00512 -0.0652 0.8629 1.0000
2.000 0.5260 0.01025 0.00500 -0.0641 0.8453 1.0000
2.250 0.5467 0.01017 0.00491 -0.0624 0.8246 1.0000
2.500 0.5674 0.01010 0.00483 -0.0606 0.8022 1.0000
2.750 0.5870 0.01008 0.00482 -0.0588 0.7791 1.0000
3.000 0.6075 0.01009 0.00480 -0.0570 0.7566 1.0000
3.250 0.6272 0.01012 0.00481 -0.0552 0.7314 1.0000
3.500 0.6459 0.01017 0.00485 -0.0531 0.7010 1.0000
3.750 0.6633 0.01026 0.00485 -0.0507 0.6621 1.0000
4.000 0.6797 0.01043 0.00489 -0.0481 0.6146 1.0000
4.250 0.6950 0.01070 0.00498 -0.0454 0.5602 1.0000
4.500 0.7078 0.01112 0.00512 -0.0423 0.4866 1.0000
4.750 0.7167 0.01181 0.00535 -0.0387 0.3851 1.0000
5.000 0.7220 0.01288 0.00583 -0.0347 0.2657 1.0000
5.250 0.7247 0.01439 0.00655 -0.0306 0.1284 1.0000
5.500 0.7291 0.01595 0.00760 -0.0265 0.0637 1.0000
5.750 0.7395 0.01696 0.00861 -0.0232 0.0509 1.0000
6.000 0.7524 0.01780 0.00950 -0.0203 0.0444 1.0000
6.250 0.7616 0.01914 0.01082 -0.0169 0.0396 1.0000
6.500 0.7774 0.01994 0.01172 -0.0146 0.0360 1.0000
6.750 0.7931 0.02107 0.01292 -0.0123 0.0336 1.0000
7.000 0.8105 0.02254 0.01441 -0.0104 0.0317 1.0000
7.250 0.8329 0.02530 0.01725 -0.0095 0.0300 1.0000
7.500 0.8513 0.02676 0.01896 -0.0076 0.0285 1.0000
7.750 0.8694 0.02836 0.02082 -0.0057 0.0272 1.0000
8.000 0.8860 0.03077 0.02356 -0.0035 0.0269 1.0000
8.250 0.8986 0.03362 0.02678 -0.0008 0.0271 1.0000
8.500 0.9069 0.03693 0.03045 0.0022 0.0278 1.0000
8.750 0.9092 0.04132 0.03519 0.0056 0.0289 1.0000
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Polar data table (+)
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