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SA7036 (sa7036-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: SA7036 (sa7036-il)
Reynolds number: 100,000
Max Cl/Cd: 54.47 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7036-il-100000-n5.txt
Download as CSV file: xf-sa7036-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7036                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4085   0.07675   0.07216  -0.0388   1.0000   0.0243
  -7.500  -0.4142   0.07331   0.06880  -0.0396   1.0000   0.0240
  -7.250  -0.4192   0.06965   0.06518  -0.0407   1.0000   0.0236
  -7.000  -0.4242   0.06588   0.06144  -0.0416   1.0000   0.0232
  -6.750  -0.4288   0.06186   0.05739  -0.0423   1.0000   0.0229
  -6.500  -0.4315   0.05780   0.05326  -0.0427   1.0000   0.0225
  -6.250  -0.4316   0.05364   0.04898  -0.0430   1.0000   0.0221
  -6.000  -0.4291   0.04911   0.04425  -0.0433   1.0000   0.0217
  -5.750  -0.4223   0.04465   0.03950  -0.0435   0.9999   0.0213
  -5.500  -0.3921   0.03859   0.03285  -0.0481   0.9943   0.0211
  -5.250  -0.3617   0.03378   0.02738  -0.0510   0.9885   0.0211
  -5.000  -0.3279   0.03012   0.02305  -0.0534   0.9838   0.0223
  -4.750  -0.2949   0.02767   0.01991  -0.0548   0.9782   0.0244
  -4.500  -0.2618   0.02488   0.01667  -0.0563   0.9734   0.0255
  -4.250  -0.2265   0.02291   0.01442  -0.0581   0.9693   0.0267
  -4.000  -0.1953   0.02150   0.01282  -0.0588   0.9628   0.0285
  -3.750  -0.1589   0.02047   0.01158  -0.0605   0.9580   0.0332
  -3.500  -0.1268   0.01924   0.01024  -0.0613   0.9517   0.0362
  -3.250  -0.0922   0.01829   0.00922  -0.0627   0.9457   0.0409
  -3.000  -0.0567   0.01743   0.00825  -0.0642   0.9401   0.0511
  -2.750  -0.0246   0.01652   0.00750  -0.0652   0.9326   0.0894
  -2.500   0.0086   0.01540   0.00707  -0.0668   0.9267   0.2317
  -2.250   0.0366   0.01451   0.00688  -0.0672   0.9182   0.4097
  -2.000   0.0653   0.01390   0.00673  -0.0670   0.9104   0.5577
  -1.750   0.0929   0.01345   0.00661  -0.0661   0.9022   0.6844
  -1.500   0.1173   0.01312   0.00651  -0.0642   0.8924   0.7902
  -1.250   0.1578   0.01283   0.00625  -0.0654   0.8865   0.8988
  -1.000   0.2133   0.01261   0.00588  -0.0707   0.8786   0.9899
  -0.750   0.2462   0.01254   0.00562  -0.0716   0.8682   1.0000
  -0.500   0.2752   0.01247   0.00537  -0.0717   0.8569   1.0000
  -0.250   0.3027   0.01243   0.00518  -0.0714   0.8443   1.0000
   0.000   0.3296   0.01240   0.00502  -0.0709   0.8307   1.0000
   0.250   0.3566   0.01238   0.00487  -0.0705   0.8167   1.0000
   0.500   0.3837   0.01236   0.00473  -0.0700   0.8021   1.0000
   0.750   0.4103   0.01237   0.00463  -0.0695   0.7865   1.0000
   1.000   0.4368   0.01240   0.00457  -0.0689   0.7700   1.0000
   1.250   0.4634   0.01243   0.00451  -0.0684   0.7531   1.0000
   1.500   0.4902   0.01248   0.00446  -0.0679   0.7359   1.0000
   1.750   0.5170   0.01255   0.00442  -0.0673   0.7184   1.0000
   2.000   0.5430   0.01265   0.00445  -0.0667   0.6994   1.0000
   2.250   0.5691   0.01277   0.00450  -0.0661   0.6799   1.0000
   2.500   0.5952   0.01291   0.00454  -0.0655   0.6605   1.0000
   2.750   0.6206   0.01308   0.00464  -0.0649   0.6397   1.0000
   3.000   0.6463   0.01327   0.00474  -0.0642   0.6194   1.0000
   3.250   0.6715   0.01348   0.00492  -0.0636   0.5982   1.0000
   3.500   0.6967   0.01372   0.00507  -0.0629   0.5771   1.0000
   3.750   0.7215   0.01397   0.00527  -0.0622   0.5547   1.0000
   4.000   0.7462   0.01425   0.00548  -0.0615   0.5329   1.0000
   4.250   0.7707   0.01454   0.00576  -0.0608   0.5103   1.0000
   4.500   0.7951   0.01486   0.00603  -0.0601   0.4884   1.0000
   4.750   0.8192   0.01519   0.00633  -0.0594   0.4664   1.0000
   5.000   0.8431   0.01555   0.00666  -0.0587   0.4445   1.0000
   5.250   0.8667   0.01594   0.00704  -0.0579   0.4226   1.0000
   5.500   0.8901   0.01634   0.00744  -0.0572   0.4003   1.0000
   5.750   0.9129   0.01679   0.00784  -0.0563   0.3780   1.0000
   6.000   0.9357   0.01724   0.00830  -0.0555   0.3550   1.0000
   6.250   0.9580   0.01773   0.00878  -0.0547   0.3327   1.0000
   6.500   0.9801   0.01825   0.00933  -0.0538   0.3111   1.0000
   6.750   1.0018   0.01880   0.00990  -0.0529   0.2899   1.0000
   7.000   1.0230   0.01939   0.01049  -0.0520   0.2691   1.0000
   7.250   1.0438   0.02001   0.01113  -0.0510   0.2477   1.0000
   7.500   1.0639   0.02068   0.01181  -0.0500   0.2269   1.0000
   7.750   1.0836   0.02139   0.01258  -0.0489   0.2058   1.0000
   8.000   1.1023   0.02216   0.01337  -0.0478   0.1857   1.0000
   8.250   1.1206   0.02298   0.01421  -0.0466   0.1661   1.0000
   8.500   1.1381   0.02385   0.01511  -0.0454   0.1473   1.0000
   8.750   1.1541   0.02484   0.01610  -0.0440   0.1303   1.0000
   9.000   1.1699   0.02585   0.01716  -0.0425   0.1136   1.0000
   9.250   1.1843   0.02694   0.01835  -0.0410   0.0985   1.0000
   9.500   1.1970   0.02815   0.01961  -0.0393   0.0859   1.0000
   9.750   1.2077   0.02946   0.02096  -0.0374   0.0749   1.0000
  10.000   1.2151   0.03087   0.02242  -0.0351   0.0666   1.0000
  10.250   1.2228   0.03227   0.02397  -0.0328   0.0592   1.0000
  10.500   1.2257   0.03396   0.02567  -0.0304   0.0536   1.0000
  10.750   1.2321   0.03555   0.02747  -0.0283   0.0478   1.0000
  11.000   1.2329   0.03753   0.02952  -0.0262   0.0438   1.0000
  11.250   1.2356   0.03956   0.03173  -0.0244   0.0395   1.0000
  11.500   1.2370   0.04166   0.03399  -0.0229   0.0355   1.0000
  11.750   1.2322   0.04443   0.03679  -0.0216   0.0328   1.0000
  12.000   1.2335   0.04688   0.03952  -0.0207   0.0290   1.0000
  12.250   1.2310   0.04970   0.04254  -0.0203   0.0261   1.0000
  12.500   1.2233   0.05324   0.04616  -0.0203   0.0241   1.0000
  12.750   1.2183   0.05689   0.05001  -0.0204   0.0227   1.0000
  13.000   1.2132   0.06076   0.05414  -0.0209   0.0211   1.0000
  13.250   1.2060   0.06506   0.05864  -0.0219   0.0198   1.0000
  13.500   1.1973   0.06976   0.06351  -0.0235   0.0187   1.0000
  13.750   1.1876   0.07482   0.06872  -0.0257   0.0178   1.0000
  14.000   1.1775   0.08017   0.07422  -0.0279   0.0175   1.0000
  14.250   1.1658   0.08605   0.08024  -0.0308   0.0169   1.0000
  14.500   1.1538   0.09217   0.08649  -0.0337   0.0165   1.0000
  14.750   1.1414   0.09882   0.09331  -0.0371   0.0162   1.0000
  15.000   1.1284   0.10596   0.10066  -0.0410   0.0160   1.0000
  15.250   1.1147   0.11352   0.10841  -0.0453   0.0159   1.0000
  15.500   1.1004   0.12151   0.11658  -0.0498   0.0158   1.0000
  15.750   1.0862   0.12984   0.12506  -0.0547   0.0159   1.0000
  16.000   1.0722   0.13842   0.13376  -0.0597   0.0161   1.0000
  16.250   1.0576   0.14761   0.14307  -0.0651   0.0162   1.0000
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