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TSAGI 8% AIRFOIL (tsagi8-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: TSAGI 8% AIRFOIL (tsagi8-il)
Reynolds number: 500,000
Max Cl/Cd: 65.07 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-tsagi8-il-500000-n5.txt
Download as CSV file: xf-tsagi8-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: TSAGI 8% AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5721   0.08276   0.08059  -0.0110   1.0000   0.0045
  -8.750  -0.5812   0.07716   0.07505  -0.0150   1.0000   0.0046
  -8.500  -0.5923   0.07236   0.07026  -0.0187   1.0000   0.0045
  -8.250  -0.6030   0.06744   0.06531  -0.0203   1.0000   0.0045
  -8.000  -0.6087   0.06212   0.05991  -0.0219   1.0000   0.0044
  -7.750  -0.6106   0.05715   0.05484  -0.0224   1.0000   0.0042
  -7.500  -0.6135   0.05114   0.04866  -0.0220   1.0000   0.0042
  -7.250  -0.6156   0.04471   0.04199  -0.0205   1.0000   0.0041
  -7.000  -0.6196   0.03725   0.03417  -0.0174   1.0000   0.0041
  -6.750  -0.6323   0.02728   0.02345  -0.0112   1.0000   0.0040
  -6.500  -0.6270   0.02277   0.01832  -0.0072   1.0000   0.0042
  -6.250  -0.6144   0.02006   0.01517  -0.0043   1.0000   0.0044
  -6.000  -0.5985   0.01812   0.01287  -0.0019   1.0000   0.0047
  -5.750  -0.5719   0.01668   0.01114  -0.0018   0.9972   0.0050
  -5.500  -0.5429   0.01509   0.00930  -0.0023   0.9913   0.0054
  -5.250  -0.5114   0.01438   0.00852  -0.0034   0.9855   0.0061
  -5.000  -0.4805   0.01340   0.00740  -0.0041   0.9785   0.0066
  -4.750  -0.4489   0.01249   0.00633  -0.0050   0.9704   0.0071
  -4.500  -0.4160   0.01176   0.00546  -0.0062   0.9604   0.0079
  -4.250  -0.3826   0.01092   0.00448  -0.0074   0.9475   0.0092
  -4.000  -0.3483   0.01042   0.00393  -0.0089   0.9311   0.0117
  -3.750  -0.3161   0.01003   0.00342  -0.0098   0.9107   0.0140
  -3.500  -0.2885   0.00966   0.00297  -0.0096   0.8876   0.0216
  -3.250  -0.2625   0.00945   0.00267  -0.0092   0.8645   0.0299
  -2.750  -0.2128   0.00908   0.00218  -0.0078   0.8221   0.0535
  -2.500  -0.1886   0.00885   0.00198  -0.0071   0.8031   0.0873
  -2.250  -0.1641   0.00865   0.00180  -0.0064   0.7855   0.1169
  -2.000  -0.1397   0.00844   0.00164  -0.0057   0.7685   0.1570
  -1.750  -0.1157   0.00818   0.00149  -0.0050   0.7519   0.2138
  -1.500  -0.0920   0.00791   0.00137  -0.0043   0.7364   0.2800
  -1.250  -0.0708   0.00742   0.00123  -0.0031   0.7216   0.4042
  -0.750  -0.0414   0.00578   0.00112   0.0027   0.6945   0.8405
  -0.500  -0.0055   0.00578   0.00116   0.0011   0.6806   0.8887
  -0.250   0.0394   0.00590   0.00124  -0.0025   0.6663   0.9189
   0.000   0.0865   0.00614   0.00140  -0.0065   0.6521   0.9446
   0.500   0.1552   0.00653   0.00165  -0.0090   0.6254   0.9664
   0.750   0.1967   0.00669   0.00173  -0.0120   0.6116   0.9706
   1.000   0.2285   0.00679   0.00177  -0.0129   0.5977   0.9744
   1.250   0.2570   0.00687   0.00181  -0.0131   0.5839   0.9776
   1.500   0.2893   0.00693   0.00182  -0.0142   0.5697   0.9791
   1.750   0.3208   0.00700   0.00185  -0.0151   0.5550   0.9810
   2.000   0.3512   0.00708   0.00190  -0.0158   0.5381   0.9832
   2.250   0.3800   0.00719   0.00196  -0.0161   0.5192   0.9859
   2.500   0.4109   0.00730   0.00202  -0.0170   0.4991   0.9877
   2.750   0.4424   0.00742   0.00209  -0.0179   0.4747   0.9893
   3.000   0.4729   0.00759   0.00217  -0.0187   0.4430   0.9912
   3.250   0.5027   0.00776   0.00228  -0.0193   0.4135   0.9931
   3.500   0.5303   0.00815   0.00243  -0.0197   0.3491   0.9950
   3.750   0.5575   0.00882   0.00264  -0.0202   0.2387   0.9965
   4.000   0.5830   0.00978   0.00304  -0.0205   0.1114   0.9981
   4.250   0.6102   0.01052   0.00345  -0.0210   0.0405   0.9995
   4.500   0.6348   0.01098   0.00384  -0.0206   0.0181   1.0000
   4.750   0.6567   0.01138   0.00429  -0.0195   0.0126   1.0000
   5.000   0.6788   0.01172   0.00471  -0.0184   0.0109   1.0000
   5.250   0.7003   0.01210   0.00514  -0.0174   0.0090   1.0000
   5.500   0.7197   0.01281   0.00595  -0.0158   0.0076   1.0000
   5.750   0.7398   0.01338   0.00661  -0.0144   0.0071   1.0000
   6.000   0.7593   0.01402   0.00738  -0.0129   0.0065   1.0000
   6.250   0.7778   0.01476   0.00822  -0.0112   0.0061   1.0000
   6.500   0.7977   0.01528   0.00877  -0.0099   0.0054   1.0000
   6.750   0.8167   0.01588   0.00941  -0.0086   0.0050   1.0000
   7.000   0.8320   0.01704   0.01069  -0.0064   0.0046   1.0000
   7.250   0.8487   0.01806   0.01184  -0.0045   0.0044   1.0000
   7.500   0.8654   0.01914   0.01307  -0.0026   0.0042   1.0000
   7.750   0.8811   0.02052   0.01463  -0.0005   0.0039   1.0000
   8.000   0.8962   0.02207   0.01638   0.0016   0.0037   1.0000
   8.250   0.9105   0.02373   0.01826   0.0037   0.0036   1.0000
   8.500   0.9227   0.02582   0.02067   0.0061   0.0035   1.0000
   8.750   0.9328   0.02806   0.02320   0.0086   0.0034   1.0000
   9.000   0.9377   0.03116   0.02667   0.0117   0.0034   1.0000
   9.250   0.9371   0.03478   0.03068   0.0153   0.0034   1.0000
   9.500   0.9299   0.03890   0.03518   0.0191   0.0034   1.0000
   9.750   0.9183   0.04299   0.03959   0.0229   0.0034   1.0000
  10.000   0.9079   0.04556   0.04234   0.0265   0.0034   1.0000
  10.250   0.8870   0.04902   0.04599   0.0302   0.0034   1.0000
  10.500   0.8840   0.05028   0.04733   0.0311   0.0032   1.0000
  10.750   0.8801   0.05199   0.04911   0.0311   0.0031   1.0000
  11.000   0.8317   0.06267   0.06012   0.0275   0.0034   1.0000
  11.250   0.8041   0.07124   0.06885   0.0219   0.0037   1.0000
  11.500   0.7836   0.08013   0.07785   0.0153   0.0037   1.0000
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