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USA 32 AIRFOIL (usa32-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: USA 32 AIRFOIL (usa32-il)
Reynolds number: 500,000
Max Cl/Cd: 59.6 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa32-il-500000-n5.txt
Download as CSV file: xf-usa32-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750   0.2288   0.10357   0.10045  -0.1632   0.9030   0.0150
 -12.500   0.2421   0.10027   0.09712  -0.1663   0.8998   0.0149
 -12.250   0.2418   0.09528   0.09210  -0.1687   0.8953   0.0157
 -12.000   0.2608   0.09408   0.09090  -0.1704   0.8915   0.0160
 -11.750   0.2733   0.09081   0.08759  -0.1734   0.8880   0.0160
 -11.500   0.2942   0.08889   0.08563  -0.1766   0.8849   0.0167
 -11.250   0.3053   0.08621   0.08294  -0.1786   0.8809   0.0172
 -11.000   0.3128   0.08335   0.08007  -0.1802   0.8759   0.0176
 -10.750   0.3218   0.08016   0.07685  -0.1825   0.8710   0.0179
 -10.500   0.3247   0.07537   0.07201  -0.1862   0.8667   0.0188
 -10.250   0.3406   0.07498   0.07163  -0.1861   0.8623   0.0193
 -10.000   0.3466   0.07265   0.06930  -0.1868   0.8573   0.0195
  -9.750   0.3558   0.07045   0.06708  -0.1881   0.8524   0.0200
  -9.500   0.3637   0.06766   0.06425  -0.1899   0.8478   0.0202
  -9.250   0.3632   0.06515   0.06177  -0.1899   0.8427   0.0207
  -9.000   0.3338   0.05797   0.05457  -0.1918   0.8351   0.0220
  -8.750   0.3351   0.05572   0.05231  -0.1924   0.8295   0.0221
  -8.500   0.3309   0.05417   0.05079  -0.1910   0.8233   0.0223
  -8.250   0.3218   0.05225   0.04886  -0.1891   0.8159   0.0224
  -8.000   0.3169   0.05105   0.04766  -0.1865   0.8082   0.0226
  -7.750   0.3137   0.04938   0.04598  -0.1846   0.7992   0.0229
  -7.250   0.1681   0.02513   0.02079  -0.1768   0.7761   0.0242
  -7.000   0.1631   0.02299   0.01832  -0.1718   0.7638   0.0246
  -6.750   0.1593   0.02146   0.01646  -0.1661   0.7483   0.0250
  -6.500   0.1581   0.02040   0.01505  -0.1606   0.7237   0.0254
  -6.250   0.1516   0.01979   0.01404  -0.1536   0.6871   0.0256
  -5.750   0.1533   0.01866   0.01240  -0.1429   0.6493   0.0259
  -5.500   0.1634   0.01812   0.01171  -0.1394   0.6397   0.0261
  -5.250   0.1758   0.01769   0.01113  -0.1363   0.6312   0.0263
  -5.000   0.1910   0.01729   0.01061  -0.1338   0.6242   0.0266
  -4.750   0.2083   0.01687   0.01008  -0.1316   0.6190   0.0268
  -4.500   0.2260   0.01651   0.00961  -0.1295   0.6144   0.0271
  -4.250   0.2446   0.01622   0.00921  -0.1276   0.6102   0.0275
  -4.000   0.2643   0.01587   0.00876  -0.1259   0.6067   0.0279
  -3.750   0.2846   0.01557   0.00837  -0.1242   0.6031   0.0283
  -3.500   0.3050   0.01527   0.00797  -0.1226   0.5995   0.0287
  -3.250   0.3259   0.01501   0.00760  -0.1211   0.5961   0.0290
  -3.000   0.3467   0.01481   0.00729  -0.1196   0.5923   0.0292
  -2.750   0.3686   0.01461   0.00702  -0.1182   0.5893   0.0294
  -2.500   0.3902   0.01442   0.00678  -0.1168   0.5862   0.0297
  -2.250   0.4117   0.01427   0.00658  -0.1154   0.5829   0.0299
  -2.000   0.4327   0.01404   0.00633  -0.1140   0.5795   0.0300
  -1.750   0.4538   0.01381   0.00609  -0.1126   0.5764   0.0306
  -1.500   0.4752   0.01369   0.00594  -0.1112   0.5732   0.0309
  -1.250   0.4970   0.01359   0.00582  -0.1099   0.5700   0.0315
  -1.000   0.5185   0.01349   0.00572  -0.1086   0.5662   0.0318
  -0.750   0.5402   0.01340   0.00562  -0.1073   0.5626   0.0323
  -0.500   0.5612   0.01334   0.00554  -0.1059   0.5587   0.0328
  -0.250   0.5822   0.01331   0.00548  -0.1044   0.5550   0.0332
   0.000   0.6038   0.01328   0.00543  -0.1031   0.5515   0.0336
   0.250   0.6257   0.01324   0.00539  -0.1019   0.5474   0.0341
   0.500   0.6469   0.01324   0.00537  -0.1006   0.5428   0.0346
   0.750   0.6662   0.01326   0.00536  -0.0989   0.5373   0.0349
   1.000   0.6868   0.01326   0.00534  -0.0975   0.5324   0.0358
   1.250   0.7073   0.01328   0.00536  -0.0961   0.5264   0.0370
   1.500   0.7263   0.01336   0.00541  -0.0944   0.5205   0.0378
   1.750   0.7460   0.01343   0.00546  -0.0929   0.5143   0.0394
   2.000   0.7650   0.01353   0.00554  -0.0912   0.5069   0.0407
   2.250   0.7817   0.01368   0.00565  -0.0892   0.4995   0.0430
   2.500   0.7995   0.01379   0.00577  -0.0873   0.4897   0.0512
   2.750   0.8150   0.01372   0.00601  -0.0852   0.4813   0.1777
   3.000   0.8308   0.01395   0.00623  -0.0831   0.4713   0.1976
   3.250   0.8465   0.01421   0.00649  -0.0810   0.4619   0.2112
   3.500   0.8625   0.01450   0.00672  -0.0790   0.4527   0.2166
   3.750   0.8797   0.01476   0.00698  -0.0773   0.4448   0.2279
   4.000   0.8958   0.01507   0.00726  -0.0753   0.4368   0.2333
   4.250   0.9130   0.01536   0.00752  -0.0736   0.4301   0.2395
   4.500   0.9311   0.01563   0.00780  -0.0721   0.4234   0.2476
   4.750   0.9476   0.01597   0.00811  -0.0704   0.4172   0.2539
   5.000   0.9655   0.01627   0.00843  -0.0689   0.4108   0.2637
   5.250   0.9835   0.01658   0.00874  -0.0675   0.4054   0.2719
   5.500   0.9992   0.01698   0.00910  -0.0657   0.3991   0.2767
   5.750   1.0181   0.01728   0.00943  -0.0645   0.3931   0.2835
   6.000   1.0353   0.01765   0.00979  -0.0630   0.3870   0.2898
   6.250   1.0509   0.01809   0.01021  -0.0613   0.3817   0.2956
   6.500   1.0701   0.01840   0.01055  -0.0603   0.3779   0.3022
   6.750   1.0890   0.01874   0.01091  -0.0592   0.3732   0.3095
   7.000   1.1068   0.01913   0.01131  -0.0579   0.3689   0.3168
   7.250   1.1209   0.01969   0.01185  -0.0562   0.3631   0.3234
   7.500   1.1403   0.02003   0.01222  -0.0553   0.3602   0.3298
   7.750   1.1593   0.02040   0.01262  -0.0543   0.3568   0.3347
   8.000   1.1775   0.02080   0.01306  -0.0533   0.3534   0.3405
   8.250   1.1938   0.02131   0.01357  -0.0520   0.3494   0.3458
   8.500   1.2096   0.02185   0.01411  -0.0507   0.3461   0.3506
   8.750   1.2278   0.02229   0.01459  -0.0498   0.3432   0.3554
   9.000   1.2462   0.02273   0.01508  -0.0490   0.3398   0.3604
   9.250   1.2639   0.02322   0.01560  -0.0481   0.3366   0.3647
   9.500   1.2795   0.02382   0.01623  -0.0469   0.3328   0.3696
   9.750   1.2929   0.02454   0.01696  -0.0456   0.3282   0.3751
  10.000   1.3108   0.02506   0.01752  -0.0448   0.3252   0.3800
  10.250   1.3277   0.02565   0.01817  -0.0440   0.3210   0.3850
  10.500   1.3422   0.02639   0.01893  -0.0429   0.3162   0.3897
  10.750   1.3565   0.02714   0.01971  -0.0419   0.3127   0.3945
  11.000   1.3713   0.02791   0.02052  -0.0410   0.3092   0.3999
  11.250   1.3882   0.02856   0.02124  -0.0403   0.3060   0.4064
  11.500   1.4047   0.02927   0.02204  -0.0397   0.3025   0.4175
  12.000   1.5800   0.03268   0.02653  -0.0713   0.2832   1.0000
  12.250   1.5851   0.03407   0.02791  -0.0693   0.2763   1.0000
  12.500   1.5938   0.03525   0.02912  -0.0678   0.2681   1.0000
  12.750   1.5967   0.03689   0.03075  -0.0658   0.2589   1.0000
  13.000   1.5985   0.03867   0.03252  -0.0638   0.2478   1.0000
  13.250   1.5972   0.04078   0.03459  -0.0617   0.2337   1.0000
  13.500   1.5950   0.04303   0.03682  -0.0598   0.2201   1.0000
  13.750   1.5845   0.04613   0.03984  -0.0574   0.2018   1.0000
  14.250   1.5706   0.05195   0.04561  -0.0538   0.1787   1.0000
  14.500   1.5648   0.05487   0.04854  -0.0523   0.1703   1.0000
  14.750   1.5603   0.05771   0.05138  -0.0510   0.1631   1.0000
  15.000   1.5579   0.06036   0.05406  -0.0499   0.1585   1.0000
  15.250   1.5581   0.06276   0.05652  -0.0489   0.1541   1.0000
  15.500   1.5553   0.06551   0.05929  -0.0479   0.1489   1.0000
  15.750   1.5502   0.06857   0.06239  -0.0470   0.1441   1.0000
  16.000   1.5515   0.07095   0.06484  -0.0463   0.1398   1.0000
  16.250   1.5485   0.07384   0.06777  -0.0456   0.1349   1.0000
  16.500   1.5419   0.07718   0.07114  -0.0449   0.1294   1.0000
  16.750   1.5409   0.07992   0.07392  -0.0444   0.1243   1.0000
  17.000   1.5295   0.08395   0.07795  -0.0439   0.1154   1.0000
  17.250   1.5241   0.08733   0.08138  -0.0435   0.1092   1.0000
  17.500   1.5093   0.09191   0.08593  -0.0432   0.0989   1.0000
  17.750   1.5000   0.09585   0.08990  -0.0431   0.0934   1.0000
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