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USA 32 AIRFOIL (usa32-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: USA 32 AIRFOIL (usa32-il)
Reynolds number: 500,000
Max Cl/Cd: 68.86 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa32-il-500000.txt
Download as CSV file: xf-usa32-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 32 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250   0.1811   0.10783   0.10510  -0.1466   0.9419   0.0256
 -12.000   0.1818   0.10396   0.10122  -0.1509   0.9384   0.0263
 -11.750   0.1917   0.09992   0.09717  -0.1540   0.9363   0.0266
 -11.500   0.2131   0.09726   0.09450  -0.1556   0.9347   0.0268
 -11.250   0.2334   0.09447   0.09169  -0.1586   0.9332   0.0271
 -11.000   0.2545   0.09159   0.08879  -0.1623   0.9318   0.0277
 -10.750   0.2687   0.08893   0.08612  -0.1647   0.9284   0.0283
 -10.500   0.2782   0.08627   0.08345  -0.1664   0.9238   0.0295
 -10.250   0.2794   0.08034   0.07749  -0.1755   0.9196   0.0308
 -10.000   0.3045   0.07756   0.07469  -0.1782   0.9179   0.0311
  -9.750   0.3337   0.07524   0.07235  -0.1816   0.9163   0.0316
  -9.500   0.3496   0.07338   0.07047  -0.1832   0.9124   0.0322
  -9.250   0.3593   0.07129   0.06838  -0.1842   0.9074   0.0334
  -9.000   0.3586   0.06469   0.06174  -0.1944   0.9013   0.0358
  -8.750   0.3763   0.06283   0.05985  -0.1951   0.8970   0.0361
  -8.500   0.3848   0.06197   0.05900  -0.1931   0.8910   0.0365
  -8.250   0.3991   0.06003   0.05704  -0.1946   0.8861   0.0370
  -8.000   0.4144   0.05784   0.05481  -0.1972   0.8815   0.0380
  -7.750   0.4039   0.05638   0.05338  -0.1943   0.8732   0.0386
  -7.500   0.3566   0.04983   0.04677  -0.1954   0.8628   0.0413
  -7.250   0.3621   0.04934   0.04630  -0.1919   0.8568   0.0417
  -7.000   0.3786   0.04861   0.04554  -0.1911   0.8515   0.0422
  -6.750   0.3835   0.04738   0.04429  -0.1891   0.8442   0.0428
  -6.500   0.3393   0.03665   0.03330  -0.1902   0.8339   0.0479
  -6.250   0.3499   0.03704   0.03374  -0.1863   0.8255   0.0481
  -6.000   0.3660   0.03694   0.03360  -0.1842   0.8165   0.0485
  -5.750   0.3694   0.03666   0.03330  -0.1798   0.8049   0.0489
  -5.500   0.3771   0.03566   0.03225  -0.1770   0.7933   0.0497
  -5.250   0.3346   0.02589   0.02176  -0.1711   0.7799   0.0559
  -5.000   0.3358   0.02543   0.02132  -0.1656   0.7636   0.0566
  -4.750   0.3337   0.02472   0.02053  -0.1596   0.7426   0.0574
  -4.500   0.3345   0.02395   0.01958  -0.1544   0.7182   0.0589
  -4.250   0.3237   0.02218   0.01724  -0.1473   0.6962   0.0643
  -4.000   0.3340   0.02169   0.01672  -0.1439   0.6808   0.0656
  -3.750   0.3458   0.02123   0.01613  -0.1408   0.6696   0.0683
  -3.500   0.3545   0.02024   0.01485  -0.1373   0.6615   0.0748
  -3.250   0.3716   0.01974   0.01432  -0.1353   0.6544   0.0771
  -2.750   0.4005   0.01476   0.00767  -0.1267   0.6441   0.0417
  -2.500   0.4225   0.01429   0.00713  -0.1254   0.6392   0.0420
  -2.250   0.4465   0.01396   0.00670  -0.1245   0.6343   0.0422
  -2.000   0.4730   0.01366   0.00632  -0.1241   0.6294   0.0425
  -1.750   0.4941   0.01343   0.00607  -0.1226   0.6256   0.0425
  -1.500   0.5162   0.01322   0.00585  -0.1213   0.6214   0.0429
  -1.250   0.5407   0.01306   0.00564  -0.1205   0.6172   0.0434
  -1.000   0.5700   0.01294   0.00545  -0.1207   0.6128   0.0439
  -0.750   0.5904   0.01283   0.00535  -0.1191   0.6088   0.0444
  -0.500   0.6101   0.01275   0.00527  -0.1173   0.6046   0.0454
  -0.250   0.6319   0.01270   0.00520  -0.1159   0.6004   0.0464
   0.000   0.6576   0.01267   0.00511  -0.1154   0.5962   0.0470
   0.250   0.6849   0.01261   0.00500  -0.1153   0.5921   0.0481
   0.500   0.7016   0.01254   0.00497  -0.1129   0.5882   0.0493
   0.750   0.7210   0.01250   0.00493  -0.1111   0.5838   0.0519
   1.000   0.7418   0.01253   0.00490  -0.1096   0.5791   0.0538
   1.250   0.7689   0.01255   0.00488  -0.1095   0.5743   0.0590
   1.500   0.7810   0.01225   0.00500  -0.1064   0.5699   0.1789
   1.750   0.7967   0.01233   0.00516  -0.1039   0.5648   0.2122
   2.000   0.8153   0.01245   0.00528  -0.1020   0.5597   0.2280
   2.250   0.8353   0.01260   0.00539  -0.1005   0.5547   0.2390
   2.500   0.8495   0.01270   0.00555  -0.0978   0.5490   0.2473
   2.750   0.8656   0.01284   0.00567  -0.0955   0.5431   0.2535
   3.000   0.8828   0.01298   0.00579  -0.0934   0.5373   0.2612
   3.250   0.8975   0.01313   0.00598  -0.0910   0.5302   0.2679
   3.500   0.9121   0.01331   0.00612  -0.0885   0.5231   0.2726
   3.750   0.9276   0.01347   0.00629  -0.0862   0.5153   0.2779
   4.000   0.9411   0.01371   0.00653  -0.0836   0.5066   0.2856
   4.250   0.9564   0.01394   0.00675  -0.0813   0.4979   0.2914
   4.500   0.9699   0.01421   0.00699  -0.0788   0.4886   0.2977
   4.750   0.9851   0.01448   0.00726  -0.0767   0.4794   0.3031
   5.000   0.9982   0.01484   0.00753  -0.0742   0.4701   0.3091
   5.250   1.0149   0.01510   0.00780  -0.0724   0.4613   0.3146
   5.500   1.0285   0.01549   0.00814  -0.0701   0.4526   0.3204
   5.750   1.0453   0.01581   0.00845  -0.0684   0.4445   0.3273
   6.000   1.0611   0.01617   0.00877  -0.0665   0.4377   0.3332
   6.250   1.0785   0.01649   0.00910  -0.0650   0.4307   0.3402
   6.500   1.0943   0.01688   0.00945  -0.0633   0.4238   0.3473
   6.750   1.1106   0.01726   0.00983  -0.0617   0.4176   0.3539
   7.000   1.1287   0.01760   0.01018  -0.0603   0.4119   0.3613
   7.250   1.1455   0.01797   0.01055  -0.0589   0.4064   0.3681
   7.500   1.1625   0.01838   0.01092  -0.0575   0.4015   0.3753
   7.750   1.1811   0.01869   0.01131  -0.0564   0.3971   0.3819
   8.000   1.1991   0.01906   0.01169  -0.0552   0.3926   0.3887
   8.250   1.2163   0.01948   0.01209  -0.0540   0.3881   0.3953
   8.500   1.2352   0.01986   0.01249  -0.0530   0.3841   0.4027
   8.750   1.2532   0.02024   0.01294  -0.0520   0.3802   0.4096
   9.000   1.2718   0.02062   0.01338  -0.0511   0.3765   0.4180
   9.250   1.2896   0.02107   0.01385  -0.0502   0.3724   0.4282
   9.500   1.3094   0.02149   0.01429  -0.0496   0.3682   0.4464
   9.750   1.5016   0.02288   0.01682  -0.0878   0.3578   1.0000
  10.000   1.5141   0.02352   0.01743  -0.0859   0.3535   1.0000
  10.250   1.5281   0.02410   0.01803  -0.0843   0.3496   1.0000
  10.500   1.5421   0.02467   0.01866  -0.0827   0.3458   1.0000
  10.750   1.5550   0.02532   0.01934  -0.0811   0.3418   1.0000
  11.000   1.5660   0.02608   0.02008  -0.0792   0.3373   1.0000
  11.250   1.5789   0.02678   0.02078  -0.0776   0.3336   1.0000
  11.500   1.5918   0.02747   0.02157  -0.0761   0.3300   1.0000
  11.750   1.6030   0.02828   0.02241  -0.0744   0.3250   1.0000
  12.000   1.6114   0.02926   0.02338  -0.0725   0.3201   1.0000
  12.250   1.6207   0.03024   0.02441  -0.0707   0.3140   1.0000
  12.500   1.6306   0.03121   0.02543  -0.0691   0.3084   1.0000
  12.750   1.6368   0.03243   0.02663  -0.0671   0.3032   1.0000
  13.000   1.6474   0.03341   0.02768  -0.0657   0.2983   1.0000
  13.250   1.6557   0.03457   0.02890  -0.0641   0.2925   1.0000
  13.500   1.6589   0.03612   0.03043  -0.0621   0.2861   1.0000
  13.750   1.6685   0.03728   0.03167  -0.0608   0.2801   1.0000
  14.000   1.6703   0.03904   0.03344  -0.0589   0.2719   1.0000
  14.250   1.6751   0.04063   0.03508  -0.0574   0.2633   1.0000
  14.500   1.6743   0.04274   0.03719  -0.0556   0.2549   1.0000
  14.750   1.6737   0.04493   0.03939  -0.0540   0.2427   1.0000
  15.000   1.6707   0.04739   0.04185  -0.0523   0.2309   1.0000
  15.250   1.6625   0.05040   0.04483  -0.0505   0.2168   1.0000
  15.500   1.6519   0.05373   0.04813  -0.0488   0.2036   1.0000
  15.750   1.6408   0.05718   0.05157  -0.0473   0.1926   1.0000
  16.000   1.6285   0.06080   0.05516  -0.0458   0.1826   1.0000
  16.250   1.6224   0.06383   0.05822  -0.0446   0.1756   1.0000
  16.500   1.6121   0.06736   0.06176  -0.0435   0.1692   1.0000
  16.750   1.6067   0.07043   0.06487  -0.0426   0.1633   1.0000
  17.000   1.6004   0.07363   0.06810  -0.0418   0.1578   1.0000
  17.250   1.5902   0.07732   0.07182  -0.0411   0.1528   1.0000
  17.500   1.5897   0.07998   0.07455  -0.0406   0.1479   1.0000
  17.750   1.5806   0.08368   0.07828  -0.0402   0.1423   1.0000
  18.000   1.5744   0.08711   0.08175  -0.0398   0.1382   1.0000
  18.250   1.5710   0.09022   0.08492  -0.0397   0.1320   1.0000
  18.500   1.5591   0.09443   0.08915  -0.0395   0.1263   1.0000
  18.750   1.5554   0.09767   0.09245  -0.0395   0.1203   1.0000
  19.000   1.5429   0.10209   0.09688  -0.0397   0.1138   1.0000
  19.250   1.5370   0.10565   0.10049  -0.0399   0.1076   1.0000
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