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HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL (tempest3-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
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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