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S9032 (9%) (s9032-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S9032 (9%) (s9032-il)
Reynolds number: 200,000
Max Cl/Cd: 44.92 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9032-il-200000-n5.txt
Download as CSV file: xf-s9032-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9032 (9%)                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.7580   0.12903   0.12531   0.0232   1.0000   0.0210
 -13.250  -0.9177   0.08330   0.07954  -0.0026   1.0000   0.0189
 -13.000  -1.0043   0.06105   0.05672  -0.0195   1.0000   0.0173
 -12.750  -1.0152   0.05580   0.05135  -0.0234   1.0000   0.0176
 -12.500  -1.0289   0.05078   0.04614  -0.0266   1.0000   0.0177
 -12.250  -1.0396   0.04690   0.04209  -0.0282   1.0000   0.0179
 -12.000  -1.0454   0.04421   0.03927  -0.0284   1.0000   0.0183
 -11.750  -1.0523   0.04167   0.03655  -0.0273   1.0000   0.0186
 -11.500  -1.0561   0.03961   0.03431  -0.0253   1.0000   0.0191
 -11.250  -1.0548   0.03750   0.03197  -0.0236   1.0000   0.0196
 -11.000  -1.0487   0.03553   0.02976  -0.0222   1.0000   0.0204
 -10.750  -1.0393   0.03370   0.02765  -0.0208   1.0000   0.0212
 -10.500  -1.0270   0.03203   0.02571  -0.0196   1.0000   0.0219
 -10.250  -1.0142   0.03019   0.02363  -0.0183   1.0000   0.0226
 -10.000  -1.0005   0.02835   0.02163  -0.0171   1.0000   0.0234
  -9.750  -0.9836   0.02703   0.02019  -0.0161   1.0000   0.0242
  -9.500  -0.9650   0.02596   0.01901  -0.0152   1.0000   0.0253
  -9.250  -0.9454   0.02494   0.01786  -0.0143   1.0000   0.0267
  -9.000  -0.9255   0.02386   0.01662  -0.0133   1.0000   0.0279
  -8.750  -0.9052   0.02277   0.01537  -0.0124   1.0000   0.0291
  -8.500  -0.8842   0.02178   0.01423  -0.0114   1.0000   0.0300
  -8.250  -0.8651   0.02056   0.01294  -0.0104   1.0000   0.0317
  -8.000  -0.8436   0.01974   0.01205  -0.0096   1.0000   0.0336
  -7.750  -0.8212   0.01900   0.01122  -0.0088   1.0000   0.0361
  -7.500  -0.7982   0.01838   0.01047  -0.0080   1.0000   0.0391
  -7.250  -0.7765   0.01754   0.00964  -0.0072   1.0000   0.0431
  -7.000  -0.7534   0.01693   0.00896  -0.0064   1.0000   0.0477
  -6.750  -0.7303   0.01631   0.00825  -0.0056   1.0000   0.0525
  -6.500  -0.7070   0.01574   0.00768  -0.0049   1.0000   0.0587
  -6.250  -0.6834   0.01523   0.00714  -0.0042   1.0000   0.0658
  -6.000  -0.6594   0.01479   0.00667  -0.0035   1.0000   0.0745
  -5.750  -0.6358   0.01431   0.00623  -0.0028   1.0000   0.0846
  -5.500  -0.6121   0.01387   0.00579  -0.0021   1.0000   0.0961
  -5.250  -0.5883   0.01344   0.00540  -0.0013   1.0000   0.1096
  -5.000  -0.5646   0.01304   0.00504  -0.0006   1.0000   0.1250
  -4.750  -0.5409   0.01266   0.00471   0.0002   1.0000   0.1427
  -4.500  -0.5172   0.01229   0.00439   0.0010   1.0000   0.1607
  -4.250  -0.4936   0.01194   0.00411   0.0018   1.0000   0.1796
  -4.000  -0.4698   0.01163   0.00385   0.0026   1.0000   0.2007
  -3.750  -0.4464   0.01130   0.00363   0.0034   1.0000   0.2264
  -3.500  -0.4229   0.01099   0.00341   0.0042   1.0000   0.2536
  -3.250  -0.3996   0.01069   0.00324   0.0050   1.0000   0.2832
  -3.000  -0.3765   0.01040   0.00309   0.0059   1.0000   0.3166
  -2.750  -0.3536   0.01013   0.00296   0.0068   1.0000   0.3522
  -2.500  -0.3308   0.00988   0.00285   0.0078   1.0000   0.3874
  -2.250  -0.2964   0.00965   0.00278   0.0063   0.9934   0.4270
  -2.000  -0.2586   0.00941   0.00271   0.0041   0.9830   0.4687
  -1.750  -0.2230   0.00918   0.00265   0.0025   0.9705   0.5131
  -1.500  -0.1883   0.00894   0.00261   0.0013   0.9555   0.5594
  -1.250  -0.1537   0.00873   0.00257   0.0001   0.9369   0.6039
  -1.000  -0.1180   0.00855   0.00252  -0.0012   0.9144   0.6435
  -0.750  -0.0839   0.00840   0.00248  -0.0020   0.8874   0.6803
  -0.500  -0.0532   0.00829   0.00244  -0.0019   0.8569   0.7165
  -0.250  -0.0257   0.00821   0.00242  -0.0012   0.8246   0.7534
   0.000   0.0000   0.00818   0.00242   0.0000   0.7900   0.7900
   0.250   0.0257   0.00821   0.00242   0.0012   0.7533   0.8246
   0.500   0.0532   0.00829   0.00244   0.0019   0.7164   0.8570
   0.750   0.0840   0.00840   0.00248   0.0019   0.6803   0.8874
   1.000   0.1180   0.00855   0.00252   0.0011   0.6434   0.9144
   1.250   0.1538   0.00873   0.00257  -0.0001   0.6039   0.9368
   1.500   0.1884   0.00894   0.00261  -0.0013   0.5596   0.9554
   1.750   0.2230   0.00918   0.00265  -0.0026   0.5130   0.9704
   2.000   0.2586   0.00942   0.00272  -0.0041   0.4685   0.9829
   2.250   0.2964   0.00965   0.00278  -0.0063   0.4271   0.9932
   2.500   0.3312   0.00988   0.00285  -0.0078   0.3873   1.0000
   2.750   0.3540   0.01013   0.00297  -0.0069   0.3521   1.0000
   3.000   0.3769   0.01041   0.00309  -0.0060   0.3165   1.0000
   3.250   0.4000   0.01070   0.00324  -0.0051   0.2829   1.0000
   3.500   0.4233   0.01099   0.00342  -0.0043   0.2534   1.0000
   3.750   0.4468   0.01130   0.00363  -0.0034   0.2263   1.0000
   4.000   0.4703   0.01163   0.00386  -0.0026   0.2006   1.0000
   4.250   0.4940   0.01195   0.00411  -0.0018   0.1795   1.0000
   4.500   0.5176   0.01229   0.00439  -0.0011   0.1607   1.0000
   4.750   0.5412   0.01266   0.00472  -0.0003   0.1426   1.0000
   5.000   0.5650   0.01304   0.00505   0.0005   0.1249   1.0000
   5.250   0.5887   0.01344   0.00541   0.0013   0.1096   1.0000
   5.500   0.6123   0.01387   0.00579   0.0020   0.0960   1.0000
   5.750   0.6360   0.01431   0.00623   0.0027   0.0846   1.0000
   6.000   0.6596   0.01479   0.00668   0.0035   0.0745   1.0000
   6.250   0.6835   0.01523   0.00715   0.0042   0.0659   1.0000
   6.500   0.7070   0.01574   0.00768   0.0049   0.0587   1.0000
   6.750   0.7303   0.01631   0.00825   0.0056   0.0524   1.0000
   7.000   0.7533   0.01693   0.00896   0.0064   0.0477   1.0000
   7.250   0.7764   0.01754   0.00963   0.0072   0.0431   1.0000
   7.500   0.7979   0.01838   0.01047   0.0081   0.0391   1.0000
   7.750   0.8209   0.01901   0.01123   0.0088   0.0361   1.0000
   8.000   0.8432   0.01973   0.01204   0.0096   0.0336   1.0000
   8.250   0.8647   0.02056   0.01293   0.0105   0.0317   1.0000
   8.500   0.8837   0.02177   0.01422   0.0115   0.0300   1.0000
   8.750   0.9046   0.02276   0.01536   0.0125   0.0290   1.0000
   9.000   0.9248   0.02385   0.01661   0.0135   0.0280   1.0000
   9.250   0.9446   0.02493   0.01785   0.0144   0.0267   1.0000
   9.500   0.9641   0.02595   0.01900   0.0153   0.0254   1.0000
   9.750   0.9828   0.02701   0.02017   0.0163   0.0243   1.0000
  10.000   0.9996   0.02832   0.02161   0.0173   0.0235   1.0000
  10.250   1.0135   0.03010   0.02355   0.0185   0.0227   1.0000
  10.500   1.0259   0.03201   0.02569   0.0198   0.0220   1.0000
  10.750   1.0382   0.03366   0.02761   0.0210   0.0212   1.0000
  11.000   1.0478   0.03543   0.02965   0.0224   0.0203   1.0000
  11.250   1.0536   0.03745   0.03191   0.0239   0.0197   1.0000
  11.500   1.0548   0.03954   0.03423   0.0256   0.0191   1.0000
  11.750   1.0510   0.04162   0.03649   0.0276   0.0187   1.0000
  12.000   1.0444   0.04412   0.03917   0.0287   0.0183   1.0000
  12.250   1.0385   0.04684   0.04203   0.0285   0.0179   1.0000
  12.500   1.0274   0.05076   0.04613   0.0268   0.0177   1.0000
  12.750   1.0161   0.05543   0.05095   0.0238   0.0175   1.0000
  13.000   0.9911   0.06334   0.05912   0.0179   0.0177   1.0000
  13.250   0.9200   0.08256   0.07879   0.0033   0.0188   1.0000
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