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USA-35B AIRFOIL (usa35b-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: USA-35B AIRFOIL (usa35b-il)
Reynolds number: 200,000
Max Cl/Cd: 75.17 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa35b-il-200000-n5.txt
Download as CSV file: xf-usa35b-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA-35B AIRFOIL                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3519   0.08850   0.08474  -0.0415   1.0000   0.0389
 -10.250  -0.3528   0.08581   0.08211  -0.0414   1.0000   0.0387
 -10.000  -0.3580   0.08349   0.07985  -0.0404   1.0000   0.0384
  -9.750  -0.3530   0.07989   0.07628  -0.0430   0.9948   0.0380
  -9.500  -0.3405   0.07445   0.07084  -0.0501   0.9847   0.0373
  -9.250  -0.3267   0.06728   0.06362  -0.0605   0.9733   0.0366
  -9.000  -0.3139   0.05739   0.05357  -0.0735   0.9606   0.0359
  -8.750  -0.3013   0.04756   0.04343  -0.0833   0.9483   0.0361
  -8.500  -0.2903   0.03780   0.03305  -0.0895   0.9369   0.0363
  -8.250  -0.2726   0.03153   0.02612  -0.0921   0.9278   0.0363
  -8.000  -0.2524   0.02798   0.02207  -0.0927   0.9174   0.0365
  -7.750  -0.2270   0.02535   0.01898  -0.0934   0.9095   0.0369
  -7.500  -0.2030   0.02343   0.01670  -0.0933   0.8987   0.0374
  -7.250  -0.1768   0.02191   0.01481  -0.0933   0.8888   0.0382
  -7.000  -0.1501   0.02064   0.01320  -0.0931   0.8783   0.0388
  -6.750  -0.1239   0.01959   0.01188  -0.0928   0.8668   0.0392
  -6.500  -0.0973   0.01861   0.01079  -0.0926   0.8558   0.0397
  -6.250  -0.0705   0.01784   0.00991  -0.0923   0.8437   0.0401
  -6.000  -0.0439   0.01717   0.00915  -0.0919   0.8301   0.0407
  -5.750  -0.0172   0.01658   0.00845  -0.0916   0.8161   0.0413
  -5.500   0.0096   0.01603   0.00780  -0.0912   0.8019   0.0420
  -5.250   0.0365   0.01552   0.00718  -0.0908   0.7876   0.0428
  -5.000   0.0634   0.01509   0.00664  -0.0904   0.7724   0.0440
  -4.750   0.0904   0.01474   0.00615  -0.0900   0.7564   0.0453
  -4.500   0.1170   0.01433   0.00570  -0.0897   0.7406   0.0466
  -4.250   0.1439   0.01402   0.00534  -0.0893   0.7254   0.0479
  -4.000   0.1709   0.01375   0.00500  -0.0890   0.7106   0.0495
  -3.750   0.1981   0.01352   0.00467  -0.0887   0.6967   0.0513
  -3.500   0.2253   0.01330   0.00438  -0.0884   0.6840   0.0536
  -3.250   0.2526   0.01315   0.00417  -0.0882   0.6721   0.0571
  -3.000   0.2797   0.01301   0.00397  -0.0879   0.6590   0.0631
  -2.750   0.3069   0.01288   0.00380  -0.0876   0.6459   0.0729
  -2.500   0.3342   0.01274   0.00365  -0.0874   0.6344   0.0892
  -2.250   0.3615   0.01262   0.00353  -0.0872   0.6250   0.1124
  -2.000   0.3888   0.01240   0.00350  -0.0872   0.6167   0.1619
  -1.750   0.4159   0.01222   0.00348  -0.0871   0.6088   0.2321
  -1.500   0.4415   0.01163   0.00353  -0.0870   0.6015   0.4209
  -1.250   0.4625   0.01086   0.00365  -0.0854   0.5942   0.6800
  -1.000   0.4987   0.01038   0.00367  -0.0860   0.5873   0.9785
  -0.750   0.5297   0.01047   0.00366  -0.0866   0.5797   1.0000
  -0.500   0.5567   0.01062   0.00368  -0.0863   0.5729   1.0000
  -0.250   0.5839   0.01074   0.00372  -0.0861   0.5657   1.0000
   0.000   0.6110   0.01087   0.00377  -0.0858   0.5588   1.0000
   0.250   0.6381   0.01102   0.00383  -0.0855   0.5522   1.0000
   0.500   0.6653   0.01114   0.00391  -0.0853   0.5445   1.0000
   0.750   0.6923   0.01131   0.00398  -0.0850   0.5377   1.0000
   1.000   0.7195   0.01143   0.00409  -0.0848   0.5303   1.0000
   1.250   0.7464   0.01159   0.00419  -0.0845   0.5229   1.0000
   1.500   0.7734   0.01174   0.00431  -0.0842   0.5149   1.0000
   1.750   0.8001   0.01190   0.00443  -0.0839   0.5064   1.0000
   2.000   0.8266   0.01205   0.00455  -0.0836   0.4953   1.0000
   2.250   0.8524   0.01221   0.00465  -0.0831   0.4814   1.0000
   2.500   0.8780   0.01239   0.00476  -0.0826   0.4658   1.0000
   2.750   0.9037   0.01258   0.00490  -0.0821   0.4518   1.0000
   3.000   0.9294   0.01278   0.00506  -0.0817   0.4390   1.0000
   3.250   0.9552   0.01298   0.00525  -0.0812   0.4259   1.0000
   3.500   0.9807   0.01321   0.00546  -0.0808   0.4131   1.0000
   3.750   1.0058   0.01347   0.00567  -0.0802   0.4003   1.0000
   4.000   1.0306   0.01374   0.00591  -0.0797   0.3874   1.0000
   4.250   1.0550   0.01405   0.00618  -0.0790   0.3744   1.0000
   4.500   1.0794   0.01436   0.00646  -0.0784   0.3617   1.0000
   4.750   1.1034   0.01470   0.00678  -0.0778   0.3495   1.0000
   5.000   1.1269   0.01507   0.00711  -0.0771   0.3375   1.0000
   5.250   1.1498   0.01548   0.00749  -0.0763   0.3253   1.0000
   5.500   1.1723   0.01590   0.00787  -0.0754   0.3109   1.0000
   5.750   1.1942   0.01635   0.00829  -0.0745   0.2951   1.0000
   6.000   1.2153   0.01684   0.00873  -0.0735   0.2783   1.0000
   6.250   1.2362   0.01734   0.00919  -0.0725   0.2618   1.0000
   6.500   1.2569   0.01784   0.00967  -0.0714   0.2465   1.0000
   6.750   1.2771   0.01835   0.01018  -0.0703   0.2320   1.0000
   7.000   1.2965   0.01891   0.01071  -0.0691   0.2178   1.0000
   7.250   1.3145   0.01954   0.01130  -0.0678   0.2031   1.0000
   7.500   1.3317   0.02019   0.01193  -0.0663   0.1901   1.0000
   7.750   1.3483   0.02086   0.01260  -0.0647   0.1796   1.0000
   8.000   1.3625   0.02158   0.01331  -0.0629   0.1706   1.0000
   8.250   1.3769   0.02226   0.01402  -0.0610   0.1625   1.0000
   8.500   1.3892   0.02307   0.01484  -0.0589   0.1538   1.0000
   8.750   1.4005   0.02398   0.01576  -0.0569   0.1443   1.0000
   9.000   1.4133   0.02482   0.01666  -0.0551   0.1358   1.0000
   9.250   1.4236   0.02585   0.01770  -0.0532   0.1272   1.0000
   9.500   1.4330   0.02699   0.01885  -0.0514   0.1164   1.0000
   9.750   1.4417   0.02822   0.02010  -0.0496   0.1040   1.0000
  10.000   1.4478   0.02971   0.02157  -0.0478   0.0861   1.0000
  10.250   1.4473   0.03180   0.02354  -0.0458   0.0679   1.0000
  10.500   1.4473   0.03398   0.02567  -0.0441   0.0606   1.0000
  10.750   1.4484   0.03617   0.02791  -0.0427   0.0564   1.0000
  11.000   1.4483   0.03859   0.03038  -0.0415   0.0534   1.0000
  11.250   1.4506   0.04087   0.03278  -0.0406   0.0511   1.0000
  11.500   1.4508   0.04347   0.03549  -0.0399   0.0491   1.0000
  11.750   1.4485   0.04642   0.03853  -0.0394   0.0474   1.0000
  12.000   1.4438   0.04977   0.04196  -0.0391   0.0461   1.0000
  12.250   1.4441   0.05260   0.04494  -0.0389   0.0448   1.0000
  12.500   1.4426   0.05573   0.04819  -0.0388   0.0435   1.0000
  12.750   1.4396   0.05910   0.05168  -0.0389   0.0423   1.0000
  13.000   1.4350   0.06275   0.05544  -0.0392   0.0413   1.0000
  13.250   1.4285   0.06671   0.05951  -0.0396   0.0404   1.0000
  13.500   1.4201   0.07102   0.06390  -0.0403   0.0396   1.0000
  13.750   1.4154   0.07491   0.06790  -0.0409   0.0388   1.0000
  14.000   1.4120   0.07868   0.07181  -0.0415   0.0379   1.0000
  14.250   1.4077   0.08265   0.07589  -0.0423   0.0370   1.0000
  14.500   1.4030   0.08676   0.08011  -0.0432   0.0362   1.0000
  14.750   1.3978   0.09096   0.08441  -0.0442   0.0354   1.0000
  15.000   1.3921   0.09528   0.08882  -0.0453   0.0347   1.0000
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