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USA 31 AIRFOIL (usa31-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: USA 31 AIRFOIL (usa31-il)
Reynolds number: 500,000
Max Cl/Cd: 76.83 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa31-il-500000.txt
Download as CSV file: xf-usa31-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750   0.2821   0.09154   0.08871  -0.1686   0.9448   0.0293
 -10.500   0.3040   0.08878   0.08594  -0.1722   0.9441   0.0296
 -10.250   0.2990   0.08779   0.08498  -0.1686   0.9362   0.0300
 -10.000   0.3155   0.08509   0.08227  -0.1713   0.9339   0.0306
  -9.750   0.3327   0.08216   0.07933  -0.1747   0.9319   0.0317
  -9.250   0.3256   0.07536   0.07253  -0.1792   0.9196   0.0332
  -9.000   0.3450   0.07316   0.07032  -0.1800   0.9173   0.0335
  -8.750   0.3664   0.07097   0.06811  -0.1820   0.9152   0.0338
  -8.500   0.3682   0.06966   0.06682  -0.1798   0.9084   0.0341
  -8.250   0.3774   0.06774   0.06490  -0.1800   0.9032   0.0344
  -8.000   0.3936   0.06533   0.06247  -0.1822   0.8997   0.0350
  -7.750   0.3891   0.06389   0.06105  -0.1796   0.8907   0.0357
  -7.500   0.3956   0.06114   0.05827  -0.1814   0.8848   0.0370
  -7.250   0.3533   0.05607   0.05318  -0.1822   0.8701   0.0382
  -7.000   0.3632   0.05486   0.05197  -0.1802   0.8631   0.0385
  -6.750   0.3761   0.05353   0.05061  -0.1797   0.8560   0.0388
  -6.500   0.3884   0.05192   0.04897  -0.1800   0.8490   0.0391
  -6.250   0.3976   0.05042   0.04744  -0.1796   0.8407   0.0397
  -6.000   0.4097   0.04839   0.04536  -0.1807   0.8333   0.0407
  -5.500   0.4046   0.02632   0.02327  -0.1717   0.7935   0.0448
  -5.250   0.3940   0.01446   0.01072  -0.1850   0.7876   0.0506
  -5.000   0.4193   0.02664   0.02273  -0.1921   0.7956   0.0511
  -4.750   0.4404   0.02581   0.02189  -0.1913   0.7882   0.0519
  -4.500   0.4553   0.02487   0.02089  -0.1896   0.7798   0.0532
  -4.250   0.4648   0.02235   0.01783  -0.1880   0.7709   0.0586
  -4.000   0.4798   0.02158   0.01709  -0.1858   0.7618   0.0597
  -3.750   0.4957   0.02102   0.01604  -0.1839   0.7527   0.0662
  -3.500   0.5084   0.01975   0.01489  -0.1813   0.7430   0.0677
  -3.000   0.5367   0.01846   0.01334  -0.1763   0.7233   0.0772
  -2.750   0.5526   0.01800   0.01289  -0.1739   0.7136   0.0802
  -2.500   0.5596   0.01489   0.00851  -0.1670   0.7043   0.0441
  -2.250   0.5769   0.01416   0.00774  -0.1647   0.6955   0.0427
  -2.000   0.5930   0.01360   0.00708  -0.1621   0.6862   0.0417
  -1.750   0.6109   0.01321   0.00657  -0.1598   0.6776   0.0412
  -1.500   0.6289   0.01293   0.00618  -0.1576   0.6688   0.0408
  -1.250   0.6487   0.01270   0.00587  -0.1558   0.6613   0.0407
  -1.000   0.6673   0.01252   0.00563  -0.1537   0.6534   0.0406
  -0.750   0.6889   0.01240   0.00542  -0.1523   0.6463   0.0408
  -0.500   0.7065   0.01230   0.00531  -0.1501   0.6388   0.0412
  -0.250   0.7273   0.01227   0.00520  -0.1486   0.6314   0.0421
   0.000   0.7472   0.01222   0.00513  -0.1469   0.6248   0.0424
   0.250   0.7666   0.01219   0.00507  -0.1451   0.6179   0.0425
   0.500   0.7895   0.01220   0.00499  -0.1440   0.6111   0.0430
   0.750   0.8069   0.01221   0.00500  -0.1418   0.6045   0.0436
   1.000   0.8268   0.01221   0.00496  -0.1401   0.5974   0.0440
   1.250   0.8484   0.01221   0.00489  -0.1388   0.5911   0.0454
   1.500   0.8671   0.01223   0.00491  -0.1370   0.5843   0.0470
   1.750   0.8870   0.01232   0.00493  -0.1354   0.5773   0.0487
   2.000   0.9064   0.01239   0.00498  -0.1337   0.5707   0.0524
   2.250   0.9248   0.01229   0.00506  -0.1319   0.5634   0.1180
   2.500   0.9442   0.01229   0.00533  -0.1304   0.5566   0.2533
   2.750   0.9620   0.01253   0.00562  -0.1284   0.5493   0.2750
   3.000   0.9796   0.01286   0.00590  -0.1264   0.5417   0.2869
   3.250   0.9977   0.01316   0.00619  -0.1246   0.5346   0.2948
   3.500   1.0152   0.01347   0.00648  -0.1226   0.5270   0.3011
   3.750   1.0328   0.01381   0.00673  -0.1208   0.5200   0.3077
   4.000   1.0495   0.01408   0.00704  -0.1187   0.5122   0.3127
   4.250   1.0657   0.01443   0.00734  -0.1167   0.5050   0.3176
   4.500   1.0836   0.01472   0.00761  -0.1149   0.4981   0.3226
   4.750   1.1002   0.01504   0.00793  -0.1130   0.4908   0.3290
   5.000   1.1176   0.01533   0.00818  -0.1112   0.4841   0.3316
   5.250   1.1357   0.01555   0.00841  -0.1097   0.4774   0.3332
   5.500   1.1526   0.01584   0.00864  -0.1079   0.4706   0.3346
   5.750   1.1715   0.01609   0.00888  -0.1065   0.4647   0.3363
   6.000   1.1892   0.01637   0.00914  -0.1050   0.4580   0.3385
   6.250   1.2054   0.01675   0.00944  -0.1032   0.4515   0.3400
   6.500   1.2228   0.01701   0.00973  -0.1016   0.4448   0.3413
   6.750   1.2395   0.01732   0.01003  -0.1000   0.4381   0.3427
   7.000   1.2564   0.01768   0.01037  -0.0985   0.4320   0.3441
   7.250   1.2746   0.01798   0.01071  -0.0972   0.4267   0.3456
   7.500   1.2916   0.01835   0.01108  -0.0957   0.4214   0.3473
   7.750   1.3083   0.01878   0.01146  -0.0942   0.4159   0.3490
   8.000   1.3263   0.01910   0.01185  -0.0930   0.4110   0.3507
   8.250   1.3410   0.01957   0.01231  -0.0912   0.4044   0.3527
   8.500   1.3563   0.02007   0.01276  -0.0896   0.3990   0.3543
   8.750   1.3738   0.02047   0.01322  -0.0884   0.3944   0.3558
   9.000   1.3899   0.02091   0.01370  -0.0870   0.3887   0.3579
   9.250   1.4049   0.02144   0.01423  -0.0855   0.3838   0.3603
   9.500   1.4204   0.02196   0.01478  -0.0841   0.3785   0.3624
   9.750   1.4367   0.02245   0.01534  -0.0828   0.3734   0.3643
  10.000   1.4503   0.02309   0.01597  -0.0813   0.3680   0.3664
  10.250   1.4642   0.02374   0.01661  -0.0798   0.3629   0.3684
  10.500   1.4798   0.02430   0.01725  -0.0785   0.3578   0.3705
  10.750   1.4936   0.02498   0.01796  -0.0772   0.3525   0.3725
  11.000   1.5061   0.02576   0.01873  -0.0756   0.3475   0.3746
  11.250   1.5209   0.02643   0.01949  -0.0745   0.3419   0.3769
  11.500   1.5324   0.02729   0.02038  -0.0730   0.3354   0.3790
  11.750   1.5426   0.02826   0.02134  -0.0713   0.3294   0.3818
  12.000   1.5547   0.02915   0.02230  -0.0700   0.3224   0.3841
  12.250   1.5625   0.03033   0.02346  -0.0683   0.3150   0.3861
  12.500   1.5739   0.03135   0.02455  -0.0671   0.3077   0.3894
  12.750   1.5820   0.03260   0.02581  -0.0656   0.3002   0.3920
  13.000   1.5910   0.03382   0.02707  -0.0643   0.2934   0.3952
  13.250   1.5991   0.03514   0.02842  -0.0629   0.2858   0.3982
  13.500   1.6049   0.03665   0.02995  -0.0614   0.2783   0.4004
  13.750   1.6137   0.03803   0.03138  -0.0604   0.2708   0.4036
  14.000   1.6175   0.03981   0.03316  -0.0589   0.2632   0.4065
  14.250   1.6234   0.04148   0.03487  -0.0578   0.2547   0.4098
  14.500   1.6268   0.04339   0.03679  -0.0565   0.2477   0.4134
  14.750   1.6322   0.04521   0.03867  -0.0556   0.2399   0.4169
  15.000   1.6333   0.04743   0.04090  -0.0544   0.2322   0.4207
  15.250   1.6370   0.04947   0.04298  -0.0535   0.2244   0.4259
  15.500   1.6366   0.05193   0.04546  -0.0525   0.2178   0.4319
  15.750   1.6410   0.05403   0.04762  -0.0519   0.2104   0.4425
  16.000   1.7349   0.06188   0.05625  -0.0765   0.1882   1.0000
  16.250   1.7352   0.06440   0.05882  -0.0756   0.1820   1.0000
  16.500   1.7290   0.06766   0.06209  -0.0746   0.1759   1.0000
  16.750   1.7281   0.07038   0.06484  -0.0738   0.1697   1.0000
  17.000   1.7210   0.07383   0.06831  -0.0730   0.1631   1.0000
  17.250   1.7167   0.07699   0.07152  -0.0723   0.1576   1.0000
  17.500   1.7108   0.08039   0.07494  -0.0717   0.1506   1.0000
  17.750   1.7031   0.08406   0.07865  -0.0712   0.1451   1.0000
  18.000   1.6968   0.08763   0.08224  -0.0708   0.1378   1.0000
  18.250   1.6870   0.09163   0.08627  -0.0705   0.1314   1.0000
  18.500   1.6783   0.09556   0.09022  -0.0704   0.1235   1.0000
  18.750   1.6686   0.09969   0.09438  -0.0704   0.1171   1.0000
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