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SA7038 (sa7038-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SA7038 (sa7038-il)
Reynolds number: 500,000
Max Cl/Cd: 102.04 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7038-il-500000.txt
Download as CSV file: xf-sa7038-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7038                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2819   0.08304   0.08099  -0.0373   1.0000   0.0185
  -8.750  -0.2874   0.07989   0.07787  -0.0368   1.0000   0.0186
  -8.500  -0.2962   0.07720   0.07522  -0.0354   1.0000   0.0186
  -8.250  -0.3073   0.07480   0.07286  -0.0336   1.0000   0.0186
  -8.000  -0.3165   0.06753   0.06563  -0.0366   0.9983   0.0191
  -7.750  -0.3055   0.06344   0.06154  -0.0393   0.9959   0.0196
  -7.500  -0.2953   0.05903   0.05713  -0.0432   0.9930   0.0199
  -7.250  -0.2852   0.05462   0.05273  -0.0476   0.9885   0.0205
  -7.000  -0.2718   0.04845   0.04655  -0.0564   0.9844   0.0211
  -6.750  -0.2582   0.04128   0.03933  -0.0670   0.9791   0.0218
  -6.500  -0.2394   0.03326   0.03116  -0.0775   0.9749   0.0227
  -6.250  -0.2108   0.02617   0.02361  -0.0859   0.9713   0.0256
  -6.000  -0.2061   0.01795   0.01490  -0.0894   0.9624   0.0265
  -5.750  -0.1843   0.01500   0.01190  -0.0909   0.9582   0.0277
  -5.500  -0.1653   0.01333   0.01013  -0.0907   0.9510   0.0292
  -5.250  -0.1438   0.01141   0.00797  -0.0907   0.9450   0.0317
  -5.000  -0.1174   0.01194   0.00816  -0.0891   0.9378   0.0351
  -4.750  -0.1039   0.00751   0.00341  -0.0896   0.9316   0.0381
  -4.500  -0.0755   0.01561   0.01021  -0.0925   0.9405   0.0189
  -4.250  -0.0509   0.01422   0.00869  -0.0917   0.9338   0.0182
  -4.000  -0.0249   0.01282   0.00712  -0.0910   0.9288   0.0180
  -3.750  -0.0008   0.01190   0.00610  -0.0899   0.9208   0.0181
  -3.500   0.0251   0.01120   0.00529  -0.0892   0.9149   0.0184
  -3.250   0.0497   0.01034   0.00435  -0.0884   0.9067   0.0192
  -3.000   0.0758   0.00973   0.00367  -0.0877   0.9004   0.0206
  -2.750   0.1020   0.00939   0.00329  -0.0872   0.8917   0.0227
  -2.500   0.1289   0.00912   0.00296  -0.0867   0.8845   0.0255
  -2.250   0.1556   0.00865   0.00249  -0.0862   0.8752   0.0420
  -2.000   0.1815   0.00798   0.00223  -0.0859   0.8660   0.1602
  -1.750   0.2078   0.00755   0.00207  -0.0857   0.8566   0.2568
  -1.500   0.2337   0.00707   0.00197  -0.0854   0.8454   0.3836
  -1.250   0.2594   0.00663   0.00191  -0.0850   0.8339   0.5166
  -1.000   0.2844   0.00622   0.00189  -0.0843   0.8220   0.6513
  -0.750   0.3077   0.00588   0.00189  -0.0830   0.8096   0.7713
  -0.500   0.3290   0.00565   0.00186  -0.0810   0.7964   0.8647
  -0.250   0.3579   0.00552   0.00179  -0.0805   0.7826   0.9585
   0.000   0.4003   0.00550   0.00166  -0.0835   0.7670   1.0000
   0.250   0.4263   0.00558   0.00161  -0.0830   0.7500   1.0000
   0.500   0.4524   0.00567   0.00158  -0.0825   0.7323   1.0000
   0.750   0.4787   0.00578   0.00156  -0.0821   0.7144   1.0000
   1.000   0.5051   0.00589   0.00157  -0.0817   0.6956   1.0000
   1.250   0.5315   0.00602   0.00158  -0.0813   0.6769   1.0000
   1.750   0.5843   0.00630   0.00165  -0.0806   0.6391   1.0000
   2.000   0.6106   0.00646   0.00171  -0.0802   0.6194   1.0000
   2.250   0.6368   0.00663   0.00178  -0.0798   0.5996   1.0000
   2.500   0.6631   0.00680   0.00185  -0.0795   0.5789   1.0000
   3.000   0.7155   0.00717   0.00205  -0.0788   0.5380   1.0000
   3.250   0.7415   0.00738   0.00217  -0.0785   0.5175   1.0000
   3.500   0.7675   0.00758   0.00229  -0.0781   0.4974   1.0000
   3.750   0.7935   0.00780   0.00243  -0.0778   0.4770   1.0000
   4.000   0.8192   0.00804   0.00260  -0.0774   0.4556   1.0000
   4.250   0.8449   0.00828   0.00276  -0.0771   0.4335   1.0000
   4.500   0.8703   0.00854   0.00293  -0.0767   0.4119   1.0000
   4.750   0.8959   0.00880   0.00312  -0.0763   0.3911   1.0000
   5.000   0.9211   0.00909   0.00335  -0.0759   0.3711   1.0000
   5.250   0.9464   0.00937   0.00357  -0.0755   0.3499   1.0000
   5.500   0.9714   0.00968   0.00381  -0.0751   0.3302   1.0000
   5.750   0.9964   0.00999   0.00407  -0.0747   0.3107   1.0000
   6.000   1.0210   0.01033   0.00434  -0.0742   0.2901   1.0000
   6.250   1.0454   0.01069   0.00464  -0.0737   0.2696   1.0000
   6.500   1.0695   0.01108   0.00494  -0.0732   0.2477   1.0000
   6.750   1.0933   0.01147   0.00529  -0.0727   0.2289   1.0000
   7.000   1.1172   0.01187   0.00563  -0.0722   0.2098   1.0000
   7.250   1.1405   0.01231   0.00601  -0.0715   0.1911   1.0000
   7.500   1.1635   0.01276   0.00641  -0.0709   0.1736   1.0000
   7.750   1.1866   0.01320   0.00681  -0.0703   0.1577   1.0000
   8.000   1.2091   0.01369   0.00727  -0.0696   0.1409   1.0000
   8.250   1.2307   0.01425   0.00775  -0.0687   0.1231   1.0000
   8.500   1.2520   0.01482   0.00825  -0.0679   0.1069   1.0000
   8.750   1.2731   0.01538   0.00878  -0.0670   0.0918   1.0000
   9.000   1.2934   0.01600   0.00935  -0.0660   0.0777   1.0000
   9.250   1.3127   0.01667   0.00997  -0.0649   0.0640   1.0000
   9.500   1.3313   0.01739   0.01065  -0.0637   0.0518   1.0000
   9.750   1.3495   0.01809   0.01134  -0.0625   0.0430   1.0000
  10.000   1.3667   0.01885   0.01210  -0.0611   0.0360   1.0000
  10.250   1.3832   0.01961   0.01286  -0.0596   0.0300   1.0000
  10.500   1.3987   0.02038   0.01366  -0.0579   0.0239   1.0000
  10.750   1.4078   0.02143   0.01469  -0.0553   0.0166   1.0000
  11.000   1.4136   0.02267   0.01597  -0.0522   0.0120   1.0000
  11.250   1.4153   0.02420   0.01760  -0.0488   0.0099   1.0000
  11.500   1.4240   0.02527   0.01879  -0.0465   0.0092   1.0000
  11.750   1.4302   0.02654   0.02017  -0.0441   0.0084   1.0000
  12.000   1.4353   0.02793   0.02167  -0.0419   0.0080   1.0000
  12.250   1.4391   0.02948   0.02332  -0.0397   0.0076   1.0000
  12.500   1.4387   0.03145   0.02540  -0.0375   0.0072   1.0000
  12.750   1.4323   0.03404   0.02814  -0.0353   0.0069   1.0000
  13.000   1.4269   0.03677   0.03102  -0.0337   0.0067   1.0000
  13.250   1.4284   0.03902   0.03339  -0.0327   0.0065   1.0000
  13.500   1.4264   0.04177   0.03628  -0.0319   0.0063   1.0000
  13.750   1.4233   0.04481   0.03946  -0.0315   0.0063   1.0000
  14.000   1.4180   0.04833   0.04312  -0.0315   0.0062   1.0000
  14.250   1.4117   0.05216   0.04711  -0.0319   0.0061   1.0000
  14.500   1.4054   0.05622   0.05132  -0.0327   0.0060   1.0000
  14.750   1.3982   0.06063   0.05587  -0.0338   0.0059   1.0000
  15.000   1.3891   0.06552   0.06091  -0.0353   0.0059   1.0000
  15.250   1.3809   0.07051   0.06604  -0.0372   0.0058   1.0000
  15.500   1.3713   0.07592   0.07162  -0.0393   0.0058   1.0000
  15.750   1.3612   0.08160   0.07745  -0.0417   0.0058   1.0000
  16.000   1.3502   0.08763   0.08363  -0.0444   0.0057   1.0000
  16.250   1.3400   0.09370   0.08984  -0.0473   0.0057   1.0000
  16.500   1.3285   0.10021   0.09650  -0.0505   0.0056   1.0000
  16.750   1.3174   0.10680   0.10322  -0.0539   0.0056   1.0000
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