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SD7037-092-88 (sd7037-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: SD7037-092-88 (sd7037-il)
Reynolds number: 500,000
Max Cl/Cd: 90.06 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7037-il-500000-n5.txt
Download as CSV file: xf-sd7037-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7037-092-88                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4004   0.08100   0.07873  -0.0354   1.0000   0.0083
  -8.500  -0.4080   0.07711   0.07489  -0.0362   1.0000   0.0083
  -8.250  -0.4205   0.07420   0.07204  -0.0355   1.0000   0.0082
  -8.000  -0.4130   0.06771   0.06557  -0.0440   0.9908   0.0081
  -7.750  -0.3948   0.05675   0.05456  -0.0618   0.9838   0.0080
  -7.500  -0.3942   0.03379   0.03087  -0.0821   0.9711   0.0078
  -7.250  -0.3855   0.02480   0.02094  -0.0849   0.9616   0.0079
  -7.000  -0.3642   0.02170   0.01735  -0.0854   0.9560   0.0081
  -6.750  -0.3422   0.01960   0.01486  -0.0851   0.9498   0.0082
  -6.500  -0.3168   0.01823   0.01319  -0.0851   0.9454   0.0084
  -6.250  -0.2923   0.01734   0.01205  -0.0846   0.9395   0.0086
  -6.000  -0.2694   0.01563   0.01011  -0.0841   0.9336   0.0090
  -5.750  -0.2441   0.01474   0.00909  -0.0838   0.9288   0.0092
  -5.500  -0.2192   0.01391   0.00814  -0.0833   0.9221   0.0094
  -5.250  -0.1936   0.01316   0.00727  -0.0828   0.9165   0.0095
  -5.000  -0.1680   0.01250   0.00651  -0.0824   0.9103   0.0098
  -4.750  -0.1421   0.01191   0.00584  -0.0820   0.9036   0.0100
  -4.500  -0.1158   0.01138   0.00523  -0.0816   0.8974   0.0104
  -4.250  -0.0895   0.01091   0.00468  -0.0812   0.8899   0.0108
  -4.000  -0.0629   0.01050   0.00419  -0.0808   0.8830   0.0113
  -3.750  -0.0361   0.01015   0.00378  -0.0805   0.8745   0.0116
  -3.500  -0.0093   0.00975   0.00331  -0.0802   0.8661   0.0124
  -3.250   0.0177   0.00947   0.00297  -0.0799   0.8565   0.0136
  -3.000   0.0449   0.00924   0.00268  -0.0796   0.8458   0.0150
  -2.750   0.0721   0.00901   0.00239  -0.0793   0.8345   0.0166
  -2.500   0.0993   0.00878   0.00213  -0.0790   0.8219   0.0216
  -2.250   0.1262   0.00851   0.00191  -0.0788   0.8080   0.0470
  -2.000   0.1531   0.00827   0.00175  -0.0785   0.7927   0.0839
  -1.750   0.1798   0.00799   0.00161  -0.0783   0.7759   0.1424
  -1.500   0.2065   0.00779   0.00150  -0.0781   0.7581   0.1965
  -1.250   0.2330   0.00756   0.00143  -0.0779   0.7398   0.2709
  -1.000   0.2593   0.00732   0.00137  -0.0777   0.7212   0.3599
  -0.750   0.2856   0.00710   0.00134  -0.0774   0.7023   0.4485
  -0.500   0.3116   0.00689   0.00134  -0.0771   0.6832   0.5449
  -0.250   0.3375   0.00678   0.00134  -0.0767   0.6639   0.6169
   0.000   0.3632   0.00669   0.00137  -0.0761   0.6450   0.6866
   0.250   0.3882   0.00661   0.00142  -0.0754   0.6258   0.7538
   0.500   0.4126   0.00658   0.00146  -0.0744   0.6063   0.8113
   0.750   0.4359   0.00657   0.00151  -0.0731   0.5874   0.8653
   1.000   0.4599   0.00657   0.00153  -0.0720   0.5682   0.9223
   1.250   0.4977   0.00664   0.00153  -0.0740   0.5463   0.9838
   1.500   0.5268   0.00680   0.00157  -0.0743   0.5261   1.0000
   1.750   0.5534   0.00696   0.00163  -0.0740   0.5068   1.0000
   2.000   0.5798   0.00714   0.00170  -0.0738   0.4868   1.0000
   2.250   0.6062   0.00733   0.00179  -0.0735   0.4674   1.0000
   2.500   0.6327   0.00751   0.00188  -0.0732   0.4479   1.0000
   2.750   0.6591   0.00771   0.00198  -0.0730   0.4282   1.0000
   3.000   0.6853   0.00792   0.00210  -0.0727   0.4087   1.0000
   3.250   0.7116   0.00813   0.00223  -0.0724   0.3897   1.0000
   3.500   0.7379   0.00835   0.00237  -0.0722   0.3702   1.0000
   3.750   0.7639   0.00859   0.00252  -0.0719   0.3509   1.0000
   4.000   0.7899   0.00884   0.00270  -0.0716   0.3324   1.0000
   4.250   0.8159   0.00909   0.00287  -0.0713   0.3135   1.0000
   4.500   0.8417   0.00935   0.00306  -0.0710   0.2948   1.0000
   4.750   0.8673   0.00963   0.00328  -0.0707   0.2767   1.0000
   5.000   0.8928   0.00992   0.00350  -0.0704   0.2587   1.0000
   5.250   0.9184   0.01020   0.00373  -0.0700   0.2427   1.0000
   5.500   0.9437   0.01050   0.00397  -0.0697   0.2265   1.0000
   5.750   0.9689   0.01082   0.00424  -0.0693   0.2100   1.0000
   6.000   0.9935   0.01119   0.00454  -0.0689   0.1911   1.0000
   6.250   1.0176   0.01161   0.00485  -0.0684   0.1699   1.0000
   6.500   1.0417   0.01202   0.00519  -0.0679   0.1509   1.0000
   6.750   1.0657   0.01243   0.00554  -0.0674   0.1350   1.0000
   7.000   1.0894   0.01286   0.00591  -0.0668   0.1202   1.0000
   7.250   1.1129   0.01330   0.00630  -0.0663   0.1055   1.0000
   7.500   1.1360   0.01377   0.00672  -0.0657   0.0908   1.0000
   7.750   1.1584   0.01430   0.00718  -0.0650   0.0751   1.0000
   8.000   1.1806   0.01484   0.00766  -0.0642   0.0624   1.0000
   8.250   1.2023   0.01541   0.00819  -0.0634   0.0506   1.0000
   8.500   1.2230   0.01605   0.00878  -0.0625   0.0390   1.0000
   8.750   1.2436   0.01668   0.00938  -0.0616   0.0297   1.0000
   9.000   1.2635   0.01735   0.01003  -0.0605   0.0211   1.0000
   9.250   1.2814   0.01820   0.01083  -0.0592   0.0128   1.0000
   9.500   1.3002   0.01890   0.01157  -0.0580   0.0104   1.0000
   9.750   1.3184   0.01962   0.01235  -0.0567   0.0091   1.0000
  10.000   1.3356   0.02039   0.01318  -0.0553   0.0083   1.0000
  10.250   1.3531   0.02106   0.01394  -0.0539   0.0079   1.0000
  10.500   1.3691   0.02179   0.01476  -0.0523   0.0077   1.0000
  10.750   1.3823   0.02256   0.01562  -0.0503   0.0074   1.0000
  11.000   1.3938   0.02339   0.01655  -0.0481   0.0071   1.0000
  11.250   1.4041   0.02431   0.01757  -0.0458   0.0068   1.0000
  11.500   1.4131   0.02533   0.01868  -0.0436   0.0067   1.0000
  11.750   1.4208   0.02646   0.01992  -0.0413   0.0065   1.0000
  12.000   1.4262   0.02780   0.02136  -0.0390   0.0063   1.0000
  12.250   1.4297   0.02932   0.02299  -0.0368   0.0062   1.0000
  12.500   1.4309   0.03111   0.02489  -0.0346   0.0061   1.0000
  12.750   1.4293   0.03322   0.02713  -0.0326   0.0059   1.0000
  13.000   1.4307   0.03523   0.02926  -0.0311   0.0059   1.0000
  13.250   1.4329   0.03728   0.03144  -0.0300   0.0058   1.0000
  13.500   1.4324   0.03973   0.03403  -0.0291   0.0058   1.0000
  13.750   1.4303   0.04254   0.03696  -0.0286   0.0057   1.0000
  14.000   1.4301   0.04530   0.03986  -0.0284   0.0056   1.0000
  14.250   1.4253   0.04880   0.04350  -0.0286   0.0056   1.0000
  14.500   1.4205   0.05254   0.04738  -0.0293   0.0054   1.0000
  14.750   1.4146   0.05661   0.05159  -0.0303   0.0054   1.0000
  15.000   1.4088   0.06090   0.05602  -0.0317   0.0053   1.0000
  15.250   1.3997   0.06588   0.06114  -0.0335   0.0053   1.0000
  15.500   1.3898   0.07126   0.06667  -0.0357   0.0052   1.0000
  15.750   1.3791   0.07697   0.07252  -0.0382   0.0052   1.0000
  16.000   1.3667   0.08316   0.07885  -0.0411   0.0052   1.0000
  16.250   1.3554   0.08939   0.08522  -0.0441   0.0052   1.0000
  16.500   1.3428   0.09601   0.09197  -0.0474   0.0051   1.0000
  16.750   1.3301   0.10283   0.09893  -0.0509   0.0051   1.0000
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