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USA 32 AIRFOIL (usa32-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: USA 32 AIRFOIL (usa32-il)
Reynolds number: 1,000,000
Max Cl/Cd: 67.93 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa32-il-1000000-n5.txt
Download as CSV file: xf-usa32-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250   0.2317   0.08879   0.08606  -0.1726   0.8516   0.0129
 -12.000   0.2447   0.08718   0.08443  -0.1738   0.8475   0.0131
 -11.750   0.2523   0.08474   0.08199  -0.1749   0.8438   0.0132
 -10.750   0.2670   0.07165   0.06883  -0.1815   0.8249   0.0157
 -10.500   0.2798   0.07022   0.06739  -0.1824   0.8200   0.0159
 -10.250   0.2933   0.06881   0.06595  -0.1835   0.8145   0.0161
  -9.750   0.0014   0.02829   0.02493  -0.1923   0.7957   0.0195
  -9.500  -0.0011   0.02515   0.02160  -0.1904   0.7902   0.0197
  -9.250   0.0025   0.02276   0.01902  -0.1882   0.7830   0.0199
  -9.000   0.0152   0.02159   0.01771  -0.1864   0.7745   0.0201
  -8.750   0.0213   0.02016   0.01607  -0.1832   0.7628   0.0204
  -8.500   0.0232   0.01928   0.01500  -0.1785   0.7452   0.0207
  -8.250  -0.0041   0.01912   0.01450  -0.1671   0.6798   0.0207
  -8.000  -0.0111   0.01863   0.01374  -0.1603   0.6489   0.0209
  -7.750  -0.0069   0.01783   0.01274  -0.1558   0.6379   0.0212
  -7.250   0.0146   0.01655   0.01113  -0.1492   0.6248   0.0216
  -7.000   0.0307   0.01613   0.01058  -0.1468   0.6202   0.0218
  -6.750   0.0447   0.01573   0.01005  -0.1440   0.6146   0.0220
  -6.250   0.0741   0.01478   0.00893  -0.1387   0.6054   0.0224
  -6.000   0.0922   0.01447   0.00855  -0.1366   0.6009   0.0225
  -5.750   0.1100   0.01420   0.00822  -0.1345   0.5964   0.0227
  -5.500   0.1273   0.01397   0.00791  -0.1323   0.5921   0.0228
  -5.250   0.1462   0.01373   0.00761  -0.1303   0.5889   0.0230
  -5.000   0.1673   0.01352   0.00736  -0.1288   0.5866   0.0233
  -4.750   0.1878   0.01326   0.00704  -0.1272   0.5840   0.0234
  -4.500   0.2087   0.01307   0.00680  -0.1256   0.5812   0.0237
  -4.250   0.2292   0.01293   0.00660  -0.1240   0.5778   0.0240
  -4.000   0.2493   0.01276   0.00637  -0.1223   0.5750   0.0243
  -3.750   0.2691   0.01262   0.00617  -0.1205   0.5719   0.0245
  -3.500   0.2906   0.01244   0.00595  -0.1191   0.5695   0.0248
  -3.250   0.3125   0.01227   0.00575  -0.1177   0.5673   0.0250
  -3.000   0.3343   0.01212   0.00556  -0.1164   0.5649   0.0252
  -2.750   0.3560   0.01199   0.00540  -0.1150   0.5621   0.0253
  -2.500   0.3772   0.01190   0.00527  -0.1135   0.5587   0.0255
  -2.250   0.3977   0.01183   0.00515  -0.1119   0.5552   0.0256
  -2.000   0.4188   0.01174   0.00503  -0.1104   0.5523   0.0257
  -1.750   0.4410   0.01153   0.00481  -0.1092   0.5499   0.0261
  -1.500   0.4632   0.01142   0.00468  -0.1079   0.5469   0.0263
  -1.250   0.4850   0.01134   0.00459  -0.1066   0.5434   0.0266
  -1.000   0.5063   0.01132   0.00456  -0.1052   0.5394   0.0269
  -0.750   0.5262   0.01132   0.00452  -0.1036   0.5347   0.0273
  -0.500   0.5496   0.01127   0.00447  -0.1026   0.5306   0.0278
  -0.250   0.5718   0.01125   0.00443  -0.1014   0.5255   0.0281
   0.000   0.5914   0.01128   0.00443  -0.0998   0.5197   0.0284
   0.250   0.6125   0.01131   0.00443  -0.0984   0.5146   0.0288
   0.500   0.6337   0.01134   0.00444  -0.0971   0.5076   0.0292
   0.750   0.6528   0.01142   0.00448  -0.0953   0.5001   0.0294
   1.000   0.6723   0.01152   0.00454  -0.0937   0.4889   0.0297
   1.250   0.6905   0.01164   0.00461  -0.0919   0.4800   0.0302
   1.500   0.7086   0.01177   0.00469  -0.0901   0.4699   0.0305
   1.750   0.7263   0.01193   0.00480  -0.0882   0.4579   0.0314
   2.000   0.7443   0.01212   0.00493  -0.0864   0.4486   0.0319
   2.250   0.7633   0.01228   0.00506  -0.0848   0.4397   0.0327
   2.500   0.7809   0.01249   0.00523  -0.0829   0.4315   0.0340
   3.000   0.8188   0.01287   0.00555  -0.0798   0.4170   0.0368
   3.500   0.8585   0.01296   0.00590  -0.0772   0.4055   0.1613
   3.750   0.8757   0.01321   0.00618  -0.0755   0.3988   0.1884
   4.000   0.8960   0.01341   0.00639  -0.0743   0.3932   0.1983
   4.250   0.9154   0.01364   0.00662  -0.0730   0.3869   0.2061
   4.500   0.9336   0.01393   0.00689  -0.0715   0.3802   0.2161
   4.750   0.9545   0.01414   0.00710  -0.0705   0.3750   0.2215
   5.000   0.9741   0.01438   0.00736  -0.0693   0.3705   0.2298
   5.250   0.9914   0.01474   0.00769  -0.0678   0.3636   0.2352
   5.750   1.0332   0.01521   0.00819  -0.0660   0.3564   0.2468
   6.250   1.0725   0.01581   0.00883  -0.0639   0.3480   0.2663
   6.500   1.0915   0.01615   0.00917  -0.0628   0.3443   0.2726
   6.750   1.1123   0.01643   0.00947  -0.0621   0.3407   0.2799
   7.000   1.1330   0.01672   0.00980  -0.0613   0.3376   0.2891
   7.250   1.1529   0.01706   0.01014  -0.0604   0.3342   0.2959
   7.500   1.1717   0.01745   0.01055  -0.0594   0.3304   0.3038
   7.750   1.1901   0.01787   0.01099  -0.0584   0.3269   0.3113
   8.000   1.2107   0.01821   0.01135  -0.0578   0.3235   0.3169
   8.250   1.2304   0.01859   0.01176  -0.0570   0.3195   0.3238
   8.500   1.2502   0.01898   0.01216  -0.0563   0.3170   0.3295
   8.750   1.2677   0.01947   0.01266  -0.0553   0.3134   0.3333
   9.000   1.2855   0.01998   0.01319  -0.0544   0.3100   0.3377
   9.250   1.3051   0.02041   0.01364  -0.0538   0.3052   0.3420
   9.500   1.3237   0.02089   0.01414  -0.0531   0.3012   0.3461
   9.750   1.3420   0.02140   0.01467  -0.0524   0.2985   0.3497
  10.000   1.3588   0.02202   0.01531  -0.0515   0.2953   0.3533
  10.250   1.3768   0.02257   0.01589  -0.0508   0.2911   0.3573
  10.500   1.3957   0.02308   0.01644  -0.0503   0.2879   0.3626
  10.750   1.4110   0.02380   0.01716  -0.0493   0.2817   0.3655
  11.000   1.4256   0.02461   0.01798  -0.0484   0.2763   0.3693
  11.250   1.4433   0.02524   0.01864  -0.0478   0.2716   0.3732
  11.500   1.4559   0.02618   0.01957  -0.0467   0.2639   0.3763
  11.750   1.4685   0.02715   0.02054  -0.0457   0.2550   0.3799
  12.000   1.4791   0.02832   0.02169  -0.0446   0.2443   0.3844
  12.250   1.4818   0.03007   0.02336  -0.0429   0.2245   0.3886
  12.500   1.4862   0.03177   0.02500  -0.0413   0.2088   0.3933
  12.750   1.4748   0.03472   0.02780  -0.0386   0.1812   0.3993
  13.000   1.4809   0.03643   0.02952  -0.0376   0.1730   0.4074
  13.250   1.4794   0.03882   0.03188  -0.0361   0.1604   0.4165
  13.500   1.4906   0.04040   0.03354  -0.0360   0.1561   0.4454
  14.000   1.6003   0.04583   0.03999  -0.0567   0.1377   0.9996
  14.250   1.6087   0.04824   0.04241  -0.0572   0.1319   1.0000
  14.500   1.6062   0.05076   0.04492  -0.0557   0.1223   1.0000
  14.750   1.6081   0.05290   0.04709  -0.0546   0.1187   1.0000
  15.000   1.5991   0.05614   0.05029  -0.0530   0.1066   1.0000
  15.250   1.5952   0.05893   0.05309  -0.0518   0.0997   1.0000
  15.500   1.5858   0.06230   0.05645  -0.0504   0.0912   1.0000
  16.000   1.5658   0.06937   0.06351  -0.0480   0.0762   1.0000
  16.250   1.5653   0.07198   0.06618  -0.0473   0.0751   1.0000
  16.500   1.5564   0.07553   0.06975  -0.0464   0.0683   1.0000
  16.750   1.5528   0.07855   0.07281  -0.0458   0.0656   1.0000
  17.000   1.5433   0.08232   0.07660  -0.0452   0.0600   1.0000
  17.250   1.5386   0.08557   0.07989  -0.0448   0.0572   1.0000
  17.500   1.5255   0.08989   0.08421  -0.0444   0.0500   1.0000
  17.750   1.5169   0.09371   0.08807  -0.0442   0.0458   1.0000
  18.000   1.4895   0.10000   0.09433  -0.0440   0.0319   1.0000
  18.250   1.4689   0.10558   0.09992  -0.0441   0.0206   1.0000
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