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USA 31 AIRFOIL (usa31-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: USA 31 AIRFOIL (usa31-il)
Reynolds number: 500,000
Max Cl/Cd: 69.18 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa31-il-500000-n5.txt
Download as CSV file: xf-usa31-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 31 AIRFOIL                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250   0.3076   0.09165   0.08859  -0.1751   0.9258   0.0245
 -11.000   0.3094   0.08863   0.08557  -0.1767   0.9214   0.0259
 -10.750   0.3152   0.08522   0.08214  -0.1795   0.9182   0.0260
 -10.500   0.3132   0.08328   0.08022  -0.1780   0.9122   0.0261
 -10.250   0.3159   0.08082   0.07776  -0.1782   0.9069   0.0261
 -10.000   0.3256   0.07795   0.07487  -0.1800   0.9033   0.0261
  -9.750   0.3217   0.07598   0.07292  -0.1782   0.8949   0.0262
  -9.500   0.3360   0.07439   0.07133  -0.1783   0.8903   0.0264
  -9.250   0.3419   0.07255   0.06949  -0.1779   0.8834   0.0265
  -9.000   0.3563   0.07146   0.06839  -0.1777   0.8774   0.0269
  -8.750   0.3678   0.06971   0.06662  -0.1784   0.8711   0.0274
  -8.500   0.3749   0.06780   0.06469  -0.1787   0.8625   0.0280
  -7.500   0.3561   0.05524   0.05194  -0.1795   0.8204   0.0260
  -7.250   0.3604   0.05433   0.05099  -0.1781   0.8103   0.0257
  -7.000   0.3591   0.05259   0.04922  -0.1770   0.7995   0.0255
  -6.750   0.3580   0.04994   0.04650  -0.1774   0.7897   0.0254
  -6.500   0.3561   0.04723   0.04378  -0.1773   0.7795   0.0253
  -6.250   0.3471   0.04177   0.03822  -0.1794   0.7702   0.0254
  -6.000   0.3016   0.02443   0.02000  -0.1875   0.7585   0.0248
  -5.750   0.3113   0.02209   0.01729  -0.1860   0.7501   0.0250
  -5.500   0.3229   0.02071   0.01564  -0.1837   0.7402   0.0250
  -5.250   0.3355   0.01955   0.01422  -0.1813   0.7308   0.0252
  -5.000   0.3481   0.01862   0.01306  -0.1786   0.7205   0.0253
  -4.750   0.3595   0.01785   0.01209  -0.1754   0.7100   0.0254
  -4.500   0.3700   0.01719   0.01123  -0.1720   0.6988   0.0255
  -4.250   0.3819   0.01662   0.01046  -0.1688   0.6875   0.0256
  -4.000   0.3958   0.01611   0.00978  -0.1660   0.6775   0.0257
  -3.500   0.4262   0.01543   0.00873  -0.1608   0.6578   0.0261
  -3.000   0.4594   0.01457   0.00767  -0.1562   0.6416   0.0265
  -2.750   0.4770   0.01428   0.00729  -0.1542   0.6341   0.0267
  -2.500   0.4958   0.01402   0.00696  -0.1523   0.6272   0.0269
  -2.250   0.5149   0.01381   0.00667  -0.1505   0.6200   0.0270
  -2.000   0.5336   0.01366   0.00644  -0.1486   0.6133   0.0271
  -1.750   0.5542   0.01349   0.00623  -0.1470   0.6075   0.0274
  -1.500   0.5743   0.01337   0.00606  -0.1454   0.6011   0.0277
  -1.250   0.5939   0.01329   0.00591  -0.1437   0.5949   0.0278
  -1.000   0.6145   0.01320   0.00578  -0.1422   0.5890   0.0281
  -0.750   0.6349   0.01313   0.00568  -0.1406   0.5830   0.0284
  -0.500   0.6545   0.01311   0.00560  -0.1389   0.5768   0.0288
  -0.250   0.6753   0.01306   0.00553  -0.1374   0.5714   0.0290
   0.000   0.6962   0.01303   0.00547  -0.1360   0.5652   0.0293
   0.250   0.7154   0.01306   0.00545  -0.1343   0.5583   0.0296
   0.500   0.7360   0.01309   0.00544  -0.1328   0.5522   0.0300
   0.750   0.7563   0.01306   0.00541  -0.1313   0.5458   0.0304
   1.000   0.7751   0.01311   0.00541  -0.1296   0.5390   0.0312
   1.250   0.7959   0.01313   0.00543  -0.1282   0.5323   0.0318
   1.500   0.8160   0.01320   0.00546  -0.1267   0.5252   0.0323
   1.750   0.8349   0.01331   0.00552  -0.1250   0.5182   0.0328
   2.000   0.8556   0.01339   0.00557  -0.1237   0.5112   0.0334
   2.250   0.8738   0.01354   0.00568  -0.1219   0.5037   0.0340
   2.500   0.8937   0.01367   0.00577  -0.1205   0.4967   0.0348
   2.750   0.9126   0.01383   0.00589  -0.1188   0.4884   0.0359
   3.000   0.9314   0.01401   0.00603  -0.1172   0.4820   0.0375
   3.500   0.9683   0.01441   0.00640  -0.1140   0.4676   0.0485
   3.750   0.9879   0.01429   0.00675  -0.1128   0.4612   0.2498
   4.000   1.0072   0.01456   0.00703  -0.1113   0.4548   0.2649
   4.250   1.0247   0.01489   0.00733  -0.1096   0.4488   0.2744
   4.500   1.0443   0.01518   0.00762  -0.1083   0.4429   0.2845
   4.750   1.0627   0.01549   0.00790  -0.1068   0.4368   0.2892
   5.000   1.0795   0.01587   0.00826  -0.1051   0.4309   0.2938
   5.250   1.0996   0.01614   0.00855  -0.1039   0.4260   0.2980
   5.500   1.1182   0.01648   0.00887  -0.1025   0.4205   0.3029
   5.750   1.1346   0.01688   0.00923  -0.1008   0.4148   0.3064
   6.000   1.1532   0.01720   0.00954  -0.0994   0.4103   0.3076
   6.250   1.1725   0.01749   0.00985  -0.0983   0.4051   0.3090
   6.500   1.1885   0.01791   0.01025  -0.0966   0.3982   0.3102
   6.750   1.2046   0.01834   0.01067  -0.0950   0.3918   0.3113
   7.000   1.2228   0.01871   0.01106  -0.0937   0.3860   0.3129
   7.250   1.2389   0.01917   0.01150  -0.0922   0.3801   0.3143
   7.500   1.2555   0.01963   0.01196  -0.0907   0.3757   0.3157
   7.750   1.2737   0.02003   0.01238  -0.0896   0.3705   0.3179
   8.000   1.2895   0.02054   0.01289  -0.0881   0.3642   0.3195
   8.250   1.3048   0.02109   0.01343  -0.0866   0.3597   0.3210
   8.500   1.3222   0.02155   0.01391  -0.0854   0.3544   0.3226
   8.750   1.3385   0.02207   0.01445  -0.0841   0.3490   0.3240
   9.000   1.3526   0.02272   0.01509  -0.0826   0.3435   0.3252
   9.250   1.3687   0.02328   0.01569  -0.0813   0.3386   0.3269
   9.500   1.3847   0.02386   0.01630  -0.0801   0.3332   0.3281
   9.750   1.3971   0.02465   0.01709  -0.0785   0.3263   0.3297
  10.000   1.4122   0.02530   0.01777  -0.0773   0.3219   0.3312
  10.250   1.4269   0.02600   0.01850  -0.0760   0.3159   0.3329
  10.500   1.4382   0.02691   0.01940  -0.0744   0.3091   0.3347
  10.750   1.4519   0.02770   0.02023  -0.0732   0.3035   0.3365
  11.000   1.4656   0.02851   0.02107  -0.0720   0.2981   0.3382
  11.250   1.4754   0.02958   0.02213  -0.0704   0.2918   0.3405
  11.500   1.4885   0.03045   0.02304  -0.0692   0.2864   0.3421
  11.750   1.4998   0.03148   0.02410  -0.0679   0.2798   0.3439
  12.000   1.5075   0.03277   0.02540  -0.0663   0.2721   0.3456
  12.250   1.5158   0.03407   0.02671  -0.0649   0.2628   0.3474
  12.500   1.5228   0.03548   0.02813  -0.0634   0.2554   0.3488
  12.750   1.5269   0.03716   0.02978  -0.0617   0.2445   0.3505
  13.000   1.5335   0.03868   0.03133  -0.0604   0.2364   0.3527
  13.250   1.5364   0.04054   0.03318  -0.0588   0.2277   0.3541
  13.500   1.5423   0.04220   0.03486  -0.0576   0.2192   0.3560
  13.750   1.5432   0.04433   0.03697  -0.0561   0.2104   0.3574
  14.000   1.5482   0.04614   0.03881  -0.0550   0.2026   0.3590
  14.250   1.5494   0.04834   0.04103  -0.0538   0.1957   0.3602
  14.500   1.5519   0.05047   0.04318  -0.0527   0.1876   0.3623
  14.750   1.5510   0.05295   0.04567  -0.0516   0.1798   0.3639
  15.000   1.5541   0.05512   0.04788  -0.0507   0.1738   0.3657
  15.250   1.5537   0.05763   0.05041  -0.0498   0.1681   0.3681
  15.500   1.5555   0.05995   0.05278  -0.0490   0.1622   0.3707
  15.750   1.5559   0.06247   0.05533  -0.0483   0.1567   0.3721
  16.000   1.5535   0.06533   0.05822  -0.0476   0.1501   0.3743
  16.250   1.5543   0.06791   0.06086  -0.0471   0.1446   0.3764
  16.500   1.5478   0.07128   0.06423  -0.0464   0.1366   0.3780
  16.750   1.5480   0.07395   0.06696  -0.0460   0.1313   0.3804
  17.000   1.5414   0.07744   0.07046  -0.0456   0.1243   0.3822
  17.250   1.5337   0.08110   0.07414  -0.0452   0.1155   0.3840
  17.500   1.5281   0.08457   0.07762  -0.0450   0.1084   0.3858
  17.750   1.5198   0.08839   0.08147  -0.0448   0.1018   0.3874
  18.000   1.5125   0.09217   0.08528  -0.0448   0.0957   0.3893
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