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DAE-31 AIRFOIL (dae31-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: DAE-31 AIRFOIL (dae31-il)
Reynolds number: 500,000
Max Cl/Cd: 139.39 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dae31-il-500000.txt
Download as CSV file: xf-dae31-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DAE-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
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.0032   0.10014   0.09705  -0.0983   0.8514   0.0189
  -9.750   0.0057   0.09739   0.09430  -0.1003   0.8481   0.0195
  -9.500   0.0059   0.09488   0.09178  -0.1024   0.8448   0.0196
  -9.250   0.0171   0.09187   0.08876  -0.1028   0.8424   0.0197
  -9.000   0.0291   0.08944   0.08633  -0.1032   0.8400   0.0198
  -8.750   0.0391   0.08717   0.08407  -0.1037   0.8374   0.0200
  -8.500   0.0480   0.08494   0.08186  -0.1045   0.8343   0.0203
  -8.250   0.0560   0.08266   0.07958  -0.1053   0.8313   0.0205
  -8.000   0.0639   0.08039   0.07731  -0.1061   0.8284   0.0208
  -7.750   0.0710   0.07806   0.07497  -0.1069   0.8254   0.0214
  -7.500   0.0727   0.07536   0.07227  -0.1084   0.8219   0.0225
  -7.250   0.0662   0.07238   0.06935  -0.1105   0.8177   0.0227
  -7.000   0.0684   0.06981   0.06681  -0.1108   0.8140   0.0228
  -6.750   0.0812   0.06800   0.06500  -0.1102   0.8113   0.0231
  -6.500   0.0908   0.06612   0.06311  -0.1105   0.8084   0.0234
  -6.250   0.1008   0.06401   0.06097  -0.1118   0.8055   0.0238
  -6.000   0.1111   0.06163   0.05862  -0.1138   0.8023   0.0245
  -5.750   0.1242   0.05467   0.05164  -0.1266   0.7974   0.0262
  -5.500   0.1375   0.05305   0.05002  -0.1258   0.7944   0.0264
  -5.250   0.1545   0.05128   0.04823  -0.1265   0.7915   0.0267
  -5.000   0.1741   0.04892   0.04583  -0.1290   0.7887   0.0273
  -4.500   0.2267   0.03964   0.03634  -0.1417   0.7823   0.0304
  -4.250   0.2503   0.03756   0.03423  -0.1435   0.7791   0.0310
  -4.000   0.2855   0.03022   0.02645  -0.1509   0.7758   0.0342
  -3.750   0.3100   0.02898   0.02517  -0.1516   0.7730   0.0348
  -3.500   0.3373   0.02704   0.02307  -0.1529   0.7705   0.0363
  -3.250   0.3669   0.02375   0.01940  -0.1548   0.7678   0.0395
  -3.000   0.3991   0.01607   0.01051  -0.1563   0.7649   0.0273
  -2.750   0.4273   0.01492   0.00913  -0.1564   0.7616   0.0277
  -2.500   0.4558   0.01395   0.00795  -0.1564   0.7583   0.0281
  -2.250   0.4845   0.01303   0.00683  -0.1564   0.7553   0.0282
  -2.000   0.5132   0.01237   0.00602  -0.1563   0.7525   0.0289
  -1.750   0.5417   0.01196   0.00547  -0.1562   0.7493   0.0298
  -1.500   0.5692   0.01142   0.00499  -0.1562   0.7454   0.0310
  -1.250   0.5975   0.01109   0.00464  -0.1562   0.7415   0.0328
  -1.000   0.6259   0.01075   0.00430  -0.1562   0.7379   0.0354
  -0.750   0.6547   0.01050   0.00399  -0.1562   0.7346   0.0385
  -0.500   0.6828   0.01028   0.00379  -0.1562   0.7307   0.0426
  -0.250   0.7108   0.01003   0.00358  -0.1561   0.7261   0.0497
   0.000   0.7393   0.00977   0.00337  -0.1561   0.7218   0.0680
   0.250   0.7677   0.00942   0.00323  -0.1563   0.7179   0.1402
   0.500   0.7953   0.00913   0.00325  -0.1564   0.7133   0.2566
   0.750   0.8224   0.00882   0.00329  -0.1564   0.7080   0.3949
   1.000   0.8489   0.00842   0.00332  -0.1562   0.7031   0.5757
   1.250   0.8779   0.00762   0.00329  -0.1561   0.6983   1.0000
   1.500   0.9053   0.00766   0.00329  -0.1560   0.6919   1.0000
   1.750   0.9332   0.00768   0.00323  -0.1559   0.6860   1.0000
   2.000   0.9609   0.00774   0.00322  -0.1558   0.6799   1.0000
   2.250   0.9882   0.00779   0.00324  -0.1556   0.6726   1.0000
   2.500   1.0159   0.00787   0.00320  -0.1555   0.6662   1.0000
   2.750   1.0427   0.00793   0.00327  -0.1553   0.6582   1.0000
   3.000   1.0698   0.00802   0.00327  -0.1550   0.6506   1.0000
   3.250   1.0964   0.00810   0.00335  -0.1548   0.6416   1.0000
   3.750   1.1489   0.00833   0.00348  -0.1541   0.6224   1.0000
   4.000   1.1747   0.00847   0.00356  -0.1537   0.6124   1.0000
   4.250   1.2001   0.00863   0.00367  -0.1533   0.6013   1.0000
   4.500   1.2252   0.00879   0.00380  -0.1528   0.5896   1.0000
   4.750   1.2498   0.00899   0.00395  -0.1522   0.5779   1.0000
   5.000   1.2737   0.00922   0.00411  -0.1515   0.5656   1.0000
   5.250   1.2975   0.00943   0.00430  -0.1508   0.5524   1.0000
   5.500   1.3208   0.00968   0.00450  -0.1501   0.5394   1.0000
   5.750   1.3432   0.00995   0.00472  -0.1492   0.5262   1.0000
   6.000   1.3647   0.01026   0.00498  -0.1481   0.5124   1.0000
   6.250   1.3853   0.01059   0.00525  -0.1469   0.4982   1.0000
   6.500   1.4057   0.01092   0.00553  -0.1457   0.4836   1.0000
   6.750   1.4251   0.01126   0.00583  -0.1443   0.4692   1.0000
   7.000   1.4432   0.01164   0.00617  -0.1427   0.4549   1.0000
   7.250   1.4600   0.01204   0.00653  -0.1409   0.4411   1.0000
   7.500   1.4729   0.01248   0.00691  -0.1383   0.4269   1.0000
   7.750   1.4839   0.01296   0.00735  -0.1355   0.4128   1.0000
   8.000   1.4960   0.01346   0.00782  -0.1330   0.3985   1.0000
   8.250   1.5075   0.01403   0.00837  -0.1305   0.3843   1.0000
   8.500   1.5185   0.01467   0.00897  -0.1280   0.3703   1.0000
   8.750   1.5291   0.01539   0.00963  -0.1257   0.3561   1.0000
   9.000   1.5393   0.01616   0.01036  -0.1233   0.3419   1.0000
   9.250   1.5490   0.01702   0.01117  -0.1210   0.3271   1.0000
   9.500   1.5590   0.01789   0.01200  -0.1188   0.3124   1.0000
   9.750   1.5695   0.01879   0.01287  -0.1168   0.2980   1.0000
  10.000   1.5798   0.01972   0.01377  -0.1148   0.2840   1.0000
  10.250   1.5892   0.02075   0.01476  -0.1128   0.2700   1.0000
  10.500   1.5985   0.02180   0.01577  -0.1108   0.2567   1.0000
  10.750   1.6066   0.02296   0.01689  -0.1088   0.2435   1.0000
  11.000   1.6144   0.02418   0.01807  -0.1068   0.2300   1.0000
  11.250   1.6218   0.02546   0.01930  -0.1049   0.2170   1.0000
  11.500   1.6308   0.02666   0.02049  -0.1032   0.2046   1.0000
  11.750   1.6391   0.02794   0.02175  -0.1015   0.1936   1.0000
  12.000   1.6463   0.02933   0.02312  -0.0998   0.1830   1.0000
  12.500   1.6606   0.03223   0.02599  -0.0965   0.1631   1.0000
  12.750   1.6674   0.03377   0.02753  -0.0950   0.1540   1.0000
  13.000   1.6725   0.03550   0.02924  -0.0935   0.1447   1.0000
  13.250   1.6792   0.03715   0.03089  -0.0921   0.1359   1.0000
  13.500   1.6857   0.03885   0.03261  -0.0909   0.1278   1.0000
  13.750   1.6899   0.04081   0.03456  -0.0895   0.1195   1.0000
  14.000   1.6948   0.04277   0.03652  -0.0884   0.1117   1.0000
  14.250   1.7006   0.04468   0.03846  -0.0873   0.1048   1.0000
  14.500   1.7036   0.04692   0.04071  -0.0862   0.0986   1.0000
  14.750   1.7087   0.04900   0.04282  -0.0853   0.0925   1.0000
  15.000   1.7121   0.05131   0.04517  -0.0845   0.0869   1.0000
  15.250   1.7137   0.05389   0.04776  -0.0837   0.0814   1.0000
  15.500   1.7177   0.05623   0.05016  -0.0830   0.0760   1.0000
  15.750   1.7185   0.05901   0.05297  -0.0824   0.0709   1.0000
  16.000   1.7186   0.06193   0.05592  -0.0819   0.0658   1.0000
  16.250   1.7200   0.06476   0.05881  -0.0815   0.0610   1.0000
  16.500   1.7188   0.06800   0.06209  -0.0813   0.0565   1.0000
  16.750   1.7161   0.07148   0.06562  -0.0812   0.0524   1.0000
  17.000   1.7150   0.07485   0.06905  -0.0812   0.0483   1.0000
  17.250   1.7120   0.07854   0.07280  -0.0813   0.0448   1.0000
  17.500   1.7068   0.08264   0.07695  -0.0816   0.0416   1.0000
  17.750   1.7035   0.08652   0.08092  -0.0821   0.0386   1.0000
  18.000   1.6968   0.09099   0.08546  -0.0828   0.0361   1.0000
  18.250   1.6918   0.09528   0.08983  -0.0836   0.0336   1.0000
  18.500   1.6847   0.09999   0.09463  -0.0846   0.0316   1.0000
  18.750   1.6782   0.10466   0.09938  -0.0858   0.0295   1.0000
  19.000   1.6696   0.10973   0.10454  -0.0872   0.0278   1.0000
  19.250   1.6627   0.11460   0.10950  -0.0887   0.0261   1.0000
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