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USA 32 AIRFOIL (usa32-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: USA 32 AIRFOIL (usa32-il)
Reynolds number: 1,000,000
Max Cl/Cd: 76.89 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa32-il-1000000.txt
Download as CSV file: xf-usa32-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500   0.2766   0.09001   0.08767  -0.1722   0.9017   0.0200
 -11.250   0.2891   0.08753   0.08516  -0.1742   0.8975   0.0203
 -11.000   0.2872   0.08315   0.08076  -0.1776   0.8917   0.0224
 -10.750   0.3647   0.06515   0.06276  -0.1821   0.8735   0.0229
 -10.500   0.3787   0.06336   0.06095  -0.1829   0.8694   0.0232
 -10.250   0.3175   0.07459   0.07214  -0.1831   0.8784   0.0229
 -10.000   0.3294   0.07267   0.07021  -0.1841   0.8739   0.0231
  -9.750   0.3457   0.07083   0.06834  -0.1859   0.8697   0.0234
  -9.500   0.3656   0.06848   0.06594  -0.1895   0.8657   0.0237
  -9.250   0.3723   0.06657   0.06406  -0.1898   0.8614   0.0247
  -9.000   0.3553   0.05862   0.05609  -0.1963   0.8547   0.0266
  -8.750   0.3668   0.05657   0.05400  -0.1978   0.8496   0.0268
  -8.500   0.3766   0.05601   0.05346  -0.1966   0.8443   0.0270
  -8.250   0.3783   0.05402   0.05146  -0.1968   0.8372   0.0272
  -8.000   0.3811   0.05226   0.04966  -0.1969   0.8306   0.0275
  -7.750   0.3751   0.05083   0.04824  -0.1943   0.8231   0.0277
  -7.500   0.2853   0.03407   0.03116  -0.1981   0.8128   0.0307
  -7.250   0.2371   0.02605   0.02263  -0.1924   0.8035   0.0311
  -7.000   0.2504   0.02546   0.02211  -0.1898   0.7945   0.0315
  -6.750   0.2546   0.02446   0.02102  -0.1858   0.7821   0.0317
  -6.500   0.2566   0.02375   0.02022  -0.1810   0.7643   0.0320
  -6.250   0.2424   0.02304   0.01932  -0.1727   0.7319   0.0321
  -6.000   0.2152   0.02277   0.01872  -0.1615   0.6754   0.0322
  -5.750   0.2101   0.02228   0.01805  -0.1550   0.6539   0.0325
  -5.500   0.2132   0.02139   0.01698  -0.1504   0.6433   0.0329
  -5.250   0.2198   0.02043   0.01583  -0.1465   0.6361   0.0335
  -5.000   0.2348   0.02147   0.01649  -0.1432   0.6295   0.0356
  -4.750   0.2296   0.01817   0.01290  -0.1375   0.6257   0.0364
  -4.500   0.2489   0.01766   0.01239  -0.1356   0.6214   0.0349
  -4.250   0.2643   0.01745   0.01196  -0.1328   0.6172   0.0354
  -3.750   0.2892   0.01440   0.00835  -0.1260   0.6103   0.0305
  -3.500   0.3085   0.01379   0.00767  -0.1241   0.6075   0.0305
  -3.250   0.3290   0.01350   0.00729  -0.1225   0.6046   0.0306
  -3.000   0.3493   0.01331   0.00699  -0.1207   0.6012   0.0308
  -2.750   0.3685   0.01257   0.00619  -0.1189   0.5981   0.0312
  -2.500   0.3894   0.01221   0.00578  -0.1174   0.5944   0.0315
  -2.250   0.4116   0.01197   0.00553  -0.1161   0.5919   0.0319
  -2.000   0.4338   0.01180   0.00538  -0.1148   0.5896   0.0327
  -1.750   0.4554   0.01160   0.00516  -0.1134   0.5865   0.0328
  -1.500   0.4771   0.01147   0.00501  -0.1120   0.5836   0.0332
  -1.250   0.4977   0.01136   0.00487  -0.1104   0.5802   0.0335
  -1.000   0.5190   0.01129   0.00476  -0.1090   0.5766   0.0338
  -0.750   0.5415   0.01119   0.00464  -0.1078   0.5736   0.0341
  -0.500   0.5636   0.01109   0.00455  -0.1065   0.5710   0.0346
  -0.250   0.5857   0.01100   0.00446  -0.1052   0.5677   0.0349
   0.000   0.6075   0.01096   0.00440  -0.1039   0.5640   0.0352
   0.250   0.6278   0.01098   0.00438  -0.1023   0.5599   0.0356
   0.500   0.6488   0.01089   0.00425  -0.1009   0.5557   0.0365
   0.750   0.6713   0.01079   0.00417  -0.0997   0.5526   0.0381
   1.000   0.6933   0.01077   0.00416  -0.0985   0.5485   0.0386
   1.250   0.7141   0.01079   0.00416  -0.0971   0.5439   0.0393
   1.500   0.7332   0.01087   0.00419  -0.0953   0.5389   0.0405
   1.750   0.7554   0.01087   0.00420  -0.0942   0.5346   0.0416
   2.000   0.7758   0.01090   0.00423  -0.0927   0.5289   0.0441
   2.250   0.7936   0.01100   0.00431  -0.0907   0.5224   0.0480
   2.500   0.8120   0.01075   0.00444  -0.0890   0.5162   0.1894
   2.750   0.8295   0.01089   0.00460  -0.0871   0.5070   0.2108
   3.000   0.8478   0.01107   0.00476  -0.0853   0.4989   0.2210
   3.250   0.8642   0.01128   0.00495  -0.0832   0.4886   0.2292
   3.500   0.8827   0.01148   0.00512  -0.0816   0.4782   0.2345
   3.750   0.8988   0.01176   0.00534  -0.0795   0.4680   0.2392
   4.000   0.9146   0.01204   0.00559  -0.0774   0.4564   0.2463
   4.250   0.9323   0.01230   0.00583  -0.0757   0.4462   0.2523
   4.500   0.9482   0.01263   0.00609  -0.0737   0.4362   0.2569
   4.750   0.9674   0.01286   0.00633  -0.0724   0.4283   0.2644
   5.000   0.9836   0.01321   0.00664  -0.0705   0.4204   0.2721
   5.250   1.0038   0.01343   0.00688  -0.0693   0.4139   0.2806
   5.500   1.0217   0.01375   0.00718  -0.0679   0.4064   0.2891
   5.750   1.0404   0.01405   0.00747  -0.0665   0.3996   0.2965
   6.000   1.0600   0.01432   0.00776  -0.0654   0.3942   0.3042
   6.250   1.0773   0.01469   0.00810  -0.0639   0.3881   0.3112
   6.500   1.0970   0.01498   0.00841  -0.0629   0.3836   0.3193
   6.750   1.1180   0.01524   0.00868  -0.0620   0.3793   0.3264
   7.000   1.1371   0.01557   0.00901  -0.0609   0.3745   0.3322
   7.250   1.1542   0.01599   0.00943  -0.0596   0.3698   0.3386
   7.500   1.1743   0.01630   0.00975  -0.0587   0.3663   0.3444
   7.750   1.1953   0.01658   0.01006  -0.0580   0.3623   0.3500
   8.000   1.2148   0.01693   0.01043  -0.0571   0.3585   0.3561
   8.250   1.2318   0.01739   0.01087  -0.0559   0.3542   0.3606
   8.500   1.2506   0.01781   0.01131  -0.0549   0.3503   0.3654
   8.750   1.2718   0.01812   0.01166  -0.0544   0.3468   0.3702
   9.000   1.2918   0.01849   0.01205  -0.0538   0.3435   0.3750
   9.250   1.3090   0.01900   0.01256  -0.0527   0.3384   0.3793
   9.500   1.3257   0.01957   0.01314  -0.0517   0.3344   0.3842
   9.750   1.3474   0.01990   0.01352  -0.0514   0.3317   0.3894
  10.000   1.3673   0.02033   0.01397  -0.0509   0.3275   0.3938
  10.250   1.3863   0.02085   0.01453  -0.0504   0.3233   0.4008
  10.500   1.4007   0.02160   0.01527  -0.0492   0.3182   0.4068
  10.750   1.4229   0.02200   0.01574  -0.0493   0.3161   0.4154
  11.000   1.5644   0.02280   0.01765  -0.0762   0.3038   0.9960
  11.250   1.6222   0.02371   0.01858  -0.0843   0.2964   1.0000
  11.500   1.6326   0.02454   0.01940  -0.0824   0.2898   1.0000
  11.750   1.6437   0.02535   0.02021  -0.0806   0.2845   1.0000
  12.000   1.6573   0.02603   0.02091  -0.0792   0.2785   1.0000
  12.250   1.6670   0.02697   0.02186  -0.0774   0.2734   1.0000
  12.500   1.6770   0.02791   0.02279  -0.0757   0.2652   1.0000
  12.750   1.6813   0.02925   0.02408  -0.0734   0.2548   1.0000
  13.000   1.6903   0.03030   0.02514  -0.0717   0.2456   1.0000
  13.250   1.6920   0.03188   0.02667  -0.0693   0.2326   1.0000
  13.500   1.6892   0.03382   0.02855  -0.0666   0.2155   1.0000
  13.750   1.6827   0.03614   0.03079  -0.0637   0.1985   1.0000
  14.000   1.6765   0.03854   0.03313  -0.0610   0.1847   1.0000
  14.250   1.6701   0.04106   0.03561  -0.0586   0.1732   1.0000
  14.500   1.6667   0.04343   0.03797  -0.0567   0.1651   1.0000
  14.750   1.6671   0.04557   0.04013  -0.0551   0.1596   1.0000
  15.000   1.6631   0.04814   0.04271  -0.0534   0.1524   1.0000
  15.250   1.6662   0.05011   0.04472  -0.0523   0.1485   1.0000
  15.500   1.6650   0.05250   0.04713  -0.0510   0.1435   1.0000
  15.750   1.6629   0.05502   0.04967  -0.0498   0.1379   1.0000
  16.000   1.6627   0.05741   0.05209  -0.0487   0.1323   1.0000
  16.250   1.6561   0.06044   0.05512  -0.0475   0.1259   1.0000
  16.500   1.6559   0.06282   0.05754  -0.0465   0.1201   1.0000
  16.750   1.6468   0.06620   0.06091  -0.0454   0.1126   1.0000
  17.000   1.6353   0.06990   0.06459  -0.0443   0.1029   1.0000
  17.250   1.6203   0.07405   0.06873  -0.0433   0.0931   1.0000
  17.500   1.6097   0.07778   0.07247  -0.0425   0.0863   1.0000
  17.750   1.5955   0.08204   0.07673  -0.0418   0.0798   1.0000
  18.000   1.5893   0.08545   0.08019  -0.0415   0.0764   1.0000
  18.250   1.5749   0.08989   0.08465  -0.0411   0.0708   1.0000
  18.500   1.5664   0.09364   0.08843  -0.0409   0.0657   1.0000
  18.750   1.5546   0.09786   0.09268  -0.0408   0.0610   1.0000
  19.000   1.5378   0.10281   0.09763  -0.0409   0.0532   1.0000
  19.250   1.5250   0.10733   0.10216  -0.0412   0.0472   1.0000
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