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DAE-51 AIRFOIL (dae51-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: DAE-51 AIRFOIL (dae51-il)
Reynolds number: 500,000
Max Cl/Cd: 121.21 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dae51-il-500000.txt
Download as CSV file: xf-dae51-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DAE-51 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3448   0.09821   0.09600  -0.0325   1.0000   0.0191
  -8.750  -0.3423   0.09378   0.09161  -0.0375   1.0000   0.0198
  -8.500  -0.3393   0.09013   0.08800  -0.0404   1.0000   0.0199
  -8.250  -0.3270   0.08546   0.08334  -0.0459   0.9907   0.0199
  -8.000  -0.3188   0.07926   0.07715  -0.0512   0.9797   0.0204
  -7.750  -0.3039   0.07602   0.07390  -0.0542   0.9695   0.0207
  -7.500  -0.2914   0.07300   0.07086  -0.0569   0.9573   0.0211
  -7.250  -0.2807   0.06971   0.06754  -0.0601   0.9445   0.0215
  -7.000  -0.2680   0.06600   0.06380  -0.0645   0.9332   0.0222
  -6.750  -0.2522   0.06155   0.05929  -0.0704   0.9234   0.0232
  -6.250  -0.1960   0.04573   0.04294  -0.0920   0.9054   0.0259
  -6.000  -0.1829   0.03746   0.03435  -0.0972   0.8985   0.0267
  -5.750  -0.1615   0.03521   0.03204  -0.0983   0.8918   0.0273
  -5.500  -0.1388   0.03298   0.02966  -0.0994   0.8857   0.0280
  -5.250  -0.1142   0.03045   0.02694  -0.1007   0.8800   0.0293
  -5.000  -0.0860   0.02766   0.02375  -0.1017   0.8738   0.0324
  -4.750  -0.0580   0.01692   0.01154  -0.1030   0.8691   0.0209
  -4.500  -0.0301   0.01528   0.00960  -0.1031   0.8633   0.0207
  -4.250  -0.0028   0.01432   0.00852  -0.1031   0.8576   0.0216
  -4.000   0.0246   0.01366   0.00774  -0.1030   0.8527   0.0226
  -3.750   0.0528   0.01267   0.00661  -0.1030   0.8466   0.0230
  -3.500   0.0807   0.01187   0.00570  -0.1029   0.8411   0.0238
  -3.250   0.1088   0.01127   0.00499  -0.1028   0.8358   0.0248
  -3.000   0.1371   0.01084   0.00449  -0.1027   0.8296   0.0260
  -2.750   0.1650   0.01007   0.00365  -0.1028   0.8244   0.0288
  -2.500   0.1936   0.00985   0.00341  -0.1029   0.8182   0.0326
  -2.250   0.2221   0.00940   0.00292  -0.1029   0.8122   0.0381
  -2.000   0.2507   0.00910   0.00260  -0.1030   0.8065   0.0487
  -1.750   0.2794   0.00872   0.00233  -0.1032   0.7999   0.0850
  -1.500   0.3076   0.00823   0.00217  -0.1035   0.7942   0.1980
  -1.250   0.3359   0.00776   0.00213  -0.1039   0.7873   0.3384
  -1.000   0.3637   0.00734   0.00210  -0.1041   0.7809   0.4780
  -0.750   0.3911   0.00696   0.00212  -0.1041   0.7740   0.6196
  -0.500   0.4165   0.00658   0.00213  -0.1034   0.7670   0.7572
  -0.250   0.4369   0.00611   0.00208  -0.1011   0.7600   0.9419
   0.000   0.4693   0.00610   0.00198  -0.1020   0.7523   1.0000
   0.250   0.4980   0.00614   0.00195  -0.1021   0.7445   1.0000
   0.500   0.5265   0.00620   0.00191  -0.1021   0.7364   1.0000
   0.750   0.5550   0.00624   0.00190  -0.1022   0.7275   1.0000
   1.000   0.5833   0.00632   0.00188  -0.1022   0.7192   1.0000
   1.250   0.6117   0.00637   0.00189  -0.1023   0.7093   1.0000
   1.500   0.6400   0.00644   0.00191  -0.1023   0.6995   1.0000
   1.750   0.6681   0.00653   0.00192  -0.1023   0.6897   1.0000
   2.000   0.6963   0.00660   0.00196  -0.1024   0.6785   1.0000
   2.250   0.7243   0.00669   0.00201  -0.1024   0.6671   1.0000
   2.500   0.7523   0.00679   0.00206  -0.1024   0.6554   1.0000
   2.750   0.7801   0.00690   0.00212  -0.1023   0.6432   1.0000
   3.000   0.8077   0.00702   0.00220  -0.1023   0.6303   1.0000
   3.250   0.8353   0.00716   0.00229  -0.1022   0.6168   1.0000
   3.500   0.8627   0.00731   0.00239  -0.1021   0.6026   1.0000
   3.750   0.8900   0.00746   0.00250  -0.1021   0.5878   1.0000
   4.000   0.9171   0.00763   0.00264  -0.1020   0.5726   1.0000
   4.250   0.9441   0.00781   0.00279  -0.1018   0.5563   1.0000
   4.500   0.9709   0.00801   0.00294  -0.1017   0.5386   1.0000
   4.750   0.9974   0.00823   0.00313  -0.1015   0.5195   1.0000
   5.000   1.0235   0.00849   0.00332  -0.1012   0.4982   1.0000
   5.250   1.0490   0.00879   0.00353  -0.1009   0.4720   1.0000
   5.500   1.0746   0.00909   0.00376  -0.1006   0.4467   1.0000
   5.750   1.0995   0.00945   0.00404  -0.1002   0.4183   1.0000
   6.000   1.1230   0.00993   0.00436  -0.0996   0.3800   1.0000
   6.250   1.1462   0.01047   0.00472  -0.0991   0.3408   1.0000
   6.500   1.1692   0.01101   0.00511  -0.0985   0.3050   1.0000
   6.750   1.1912   0.01165   0.00557  -0.0977   0.2662   1.0000
   7.000   1.2126   0.01235   0.00608  -0.0970   0.2258   1.0000
   7.250   1.2335   0.01308   0.00662  -0.0961   0.1878   1.0000
   7.500   1.2533   0.01389   0.00722  -0.0951   0.1499   1.0000
   7.750   1.2720   0.01479   0.00791  -0.0940   0.1123   1.0000
   8.000   1.2898   0.01573   0.00865  -0.0927   0.0792   1.0000
   8.250   1.3071   0.01669   0.00946  -0.0914   0.0553   1.0000
   8.500   1.3244   0.01761   0.01030  -0.0899   0.0414   1.0000
   8.750   1.3403   0.01860   0.01127  -0.0883   0.0334   1.0000
   9.000   1.3594   0.01924   0.01199  -0.0871   0.0300   1.0000
   9.250   1.3729   0.02031   0.01307  -0.0851   0.0264   1.0000
   9.500   1.3882   0.02111   0.01396  -0.0833   0.0244   1.0000
   9.750   1.4017   0.02187   0.01478  -0.0813   0.0226   1.0000
  10.000   1.4121   0.02288   0.01584  -0.0790   0.0211   1.0000
  10.250   1.4118   0.02470   0.01777  -0.0755   0.0196   1.0000
  10.500   1.4238   0.02569   0.01886  -0.0737   0.0189   1.0000
  10.750   1.4336   0.02688   0.02014  -0.0718   0.0181   1.0000
  11.000   1.4427   0.02816   0.02151  -0.0700   0.0172   1.0000
  11.250   1.4512   0.02953   0.02294  -0.0682   0.0164   1.0000
  11.500   1.4563   0.03123   0.02470  -0.0664   0.0157   1.0000
  11.750   1.4521   0.03385   0.02743  -0.0638   0.0150   1.0000
  12.000   1.4557   0.03586   0.02955  -0.0620   0.0146   1.0000
  12.250   1.4623   0.03761   0.03144  -0.0606   0.0142   1.0000
  12.500   1.4673   0.03956   0.03350  -0.0592   0.0138   1.0000
  12.750   1.4714   0.04165   0.03570  -0.0578   0.0134   1.0000
  13.000   1.4746   0.04387   0.03804  -0.0565   0.0131   1.0000
  13.250   1.4772   0.04618   0.04047  -0.0554   0.0128   1.0000
  13.500   1.4791   0.04862   0.04301  -0.0544   0.0125   1.0000
  13.750   1.4802   0.05119   0.04568  -0.0535   0.0122   1.0000
  14.000   1.4802   0.05390   0.04849  -0.0527   0.0119   1.0000
  14.250   1.4785   0.05688   0.05156  -0.0519   0.0117   1.0000
  14.500   1.4736   0.06032   0.05512  -0.0510   0.0114   1.0000
  14.750   1.4623   0.06476   0.05974  -0.0495   0.0111   1.0000
  15.000   1.4591   0.06825   0.06341  -0.0498   0.0110   1.0000
  15.250   1.4545   0.07209   0.06743  -0.0503   0.0108   1.0000
  15.500   1.4482   0.07629   0.07180  -0.0509   0.0107   1.0000
  15.750   1.4401   0.08089   0.07658  -0.0518   0.0106   1.0000
  16.000   1.4307   0.08588   0.08175  -0.0530   0.0105   1.0000
  16.250   1.4195   0.09132   0.08738  -0.0546   0.0104   1.0000
  16.500   1.4069   0.09716   0.09340  -0.0567   0.0104   1.0000
  16.750   1.3930   0.10346   0.09988  -0.0591   0.0103   1.0000
  17.000   1.3779   0.11024   0.10684  -0.0621   0.0103   1.0000
  17.250   1.3619   0.11748   0.11427  -0.0657   0.0103   1.0000
  17.500   1.3448   0.12521   0.12218  -0.0698   0.0103   1.0000
  17.750   1.3263   0.13360   0.13075  -0.0745   0.0103   1.0000
  18.000   1.3073   0.14259   0.13991  -0.0800   0.0103   1.0000
  18.250   1.2874   0.15230   0.14979  -0.0861   0.0104   1.0000
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