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DAE-51 AIRFOIL (dae51-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: DAE-51 AIRFOIL (dae51-il)
Reynolds number: 100,000
Max Cl/Cd: 62.55 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dae51-il-100000.txt
Download as CSV file: xf-dae51-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3478   0.10365   0.09893  -0.0389   1.0000   0.0812
  -8.250  -0.3653   0.10299   0.09843  -0.0397   1.0000   0.0816
  -8.000  -0.3845   0.10228   0.09785  -0.0393   1.0000   0.0818
  -7.750  -0.3435   0.09416   0.08963  -0.0349   1.0000   0.0851
  -7.500  -0.3524   0.09278   0.08834  -0.0318   1.0000   0.0866
  -7.250  -0.3694   0.09202   0.08767  -0.0279   1.0000   0.0875
  -7.000  -0.3844   0.09094   0.08669  -0.0251   1.0000   0.0887
  -6.750  -0.3966   0.08947   0.08529  -0.0235   1.0000   0.0904
  -6.500  -0.4074   0.08769   0.08359  -0.0234   1.0000   0.0925
  -6.250  -0.4178   0.08537   0.08128  -0.0331   1.0000   0.0956
  -6.000  -0.4181   0.08118   0.07710  -0.0354   1.0000   0.0969
  -5.750  -0.4171   0.07879   0.07478  -0.0294   1.0000   0.0986
  -5.500  -0.4142   0.07663   0.07265  -0.0270   1.0000   0.1014
  -5.250  -0.3822   0.07044   0.06624  -0.0423   0.9963   0.1119
  -5.000  -0.3637   0.06799   0.06388  -0.0394   0.9922   0.1176
  -4.750  -0.3268   0.06284   0.05859  -0.0486   0.9863   0.1298
  -4.500  -0.2903   0.05832   0.05391  -0.0563   0.9807   0.1436
  -4.250  -0.2550   0.05448   0.04992  -0.0620   0.9748   0.1587
  -4.000  -0.2182   0.05111   0.04646  -0.0666   0.9702   0.1759
  -3.750  -0.1842   0.04802   0.04317  -0.0717   0.9631   0.2026
  -3.500  -0.0968   0.03431   0.02752  -0.0867   0.9619   0.0856
  -3.250  -0.0474   0.03101   0.02344  -0.0908   0.9585   0.0791
  -3.000  -0.0070   0.02850   0.02043  -0.0934   0.9535   0.0770
  -2.750   0.0337   0.02653   0.01799  -0.0956   0.9481   0.0766
  -2.500   0.0797   0.02535   0.01634  -0.0986   0.9438   0.0818
  -2.250   0.1152   0.02389   0.01492  -0.1003   0.9377   0.0892
  -2.000   0.1547   0.02282   0.01385  -0.1025   0.9320   0.1023
  -1.750   0.2013   0.02170   0.01288  -0.1060   0.9281   0.1379
  -1.500   0.2351   0.01921   0.01250  -0.1077   0.9228   0.5874
  -1.250   0.2602   0.01835   0.01232  -0.1052   0.9157   1.0000
  -1.000   0.2947   0.01860   0.01224  -0.1067   0.9075   1.0000
  -0.750   0.3352   0.01874   0.01208  -0.1092   0.9006   1.0000
  -0.500   0.3671   0.01900   0.01213  -0.1101   0.8920   1.0000
  -0.250   0.4057   0.01909   0.01203  -0.1120   0.8852   1.0000
   0.000   0.4338   0.01937   0.01217  -0.1122   0.8755   1.0000
   0.250   0.4726   0.01936   0.01202  -0.1138   0.8694   1.0000
   0.500   0.4980   0.01967   0.01223  -0.1135   0.8588   1.0000
   0.750   0.5365   0.01956   0.01202  -0.1148   0.8534   1.0000
   1.000   0.5603   0.01988   0.01227  -0.1141   0.8420   1.0000
   1.250   0.5886   0.02005   0.01238  -0.1140   0.8328   1.0000
   1.500   0.6211   0.01997   0.01226  -0.1142   0.8253   1.0000
   1.750   0.6461   0.02022   0.01247  -0.1136   0.8144   1.0000
   2.000   0.6804   0.01995   0.01217  -0.1137   0.8087   1.0000
   2.250   0.7045   0.02019   0.01241  -0.1129   0.7968   1.0000
   2.500   0.7304   0.02032   0.01255  -0.1122   0.7862   1.0000
   2.750   0.7627   0.02000   0.01220  -0.1119   0.7794   1.0000
   3.000   0.7873   0.02016   0.01239  -0.1110   0.7673   1.0000
   3.250   0.8133   0.02021   0.01248  -0.1102   0.7561   1.0000
   3.500   0.8432   0.01995   0.01223  -0.1096   0.7475   1.0000
   3.750   0.8705   0.01983   0.01214  -0.1088   0.7364   1.0000
   4.000   0.8962   0.01984   0.01222  -0.1078   0.7238   1.0000
   4.250   0.9227   0.01977   0.01220  -0.1069   0.7114   1.0000
   4.500   0.9499   0.01964   0.01211  -0.1060   0.6990   1.0000
   4.750   0.9774   0.01946   0.01197  -0.1052   0.6862   1.0000
   5.000   1.0046   0.01930   0.01189  -0.1042   0.6723   1.0000
   5.250   1.0310   0.01920   0.01183  -0.1032   0.6570   1.0000
   5.500   1.0571   0.01911   0.01180  -0.1022   0.6405   1.0000
   5.750   1.0833   0.01901   0.01177  -0.1012   0.6228   1.0000
   6.000   1.1100   0.01887   0.01163  -0.1001   0.6041   1.0000
   6.250   1.1337   0.01893   0.01176  -0.0988   0.5816   1.0000
   6.500   1.1588   0.01890   0.01170  -0.0975   0.5582   1.0000
   6.750   1.1811   0.01902   0.01186  -0.0960   0.5304   1.0000
   7.000   1.2023   0.01922   0.01204  -0.0944   0.5000   1.0000
   7.250   1.2214   0.01955   0.01240  -0.0926   0.4655   1.0000
   7.500   1.2394   0.01999   0.01277  -0.0906   0.4281   1.0000
   7.750   1.2547   0.02062   0.01333  -0.0885   0.3850   1.0000
   8.000   1.2673   0.02149   0.01404  -0.0861   0.3366   1.0000
   8.250   1.2758   0.02270   0.01499  -0.0833   0.2820   1.0000
   8.500   1.2794   0.02438   0.01630  -0.0801   0.2207   1.0000
   8.750   1.2779   0.02659   0.01803  -0.0764   0.1664   1.0000
   9.000   1.2764   0.02882   0.01994  -0.0726   0.1304   1.0000
   9.250   1.2769   0.03095   0.02188  -0.0691   0.1098   1.0000
   9.500   1.2817   0.03295   0.02382  -0.0663   0.0950   1.0000
   9.750   1.2903   0.03499   0.02578  -0.0640   0.0846   1.0000
  10.000   1.3058   0.03716   0.02779  -0.0625   0.0762   1.0000
  10.250   1.3212   0.03898   0.02982  -0.0608   0.0694   1.0000
  10.500   1.3520   0.04182   0.03251  -0.0611   0.0632   1.0000
  10.750   1.3711   0.04407   0.03511  -0.0598   0.0596   1.0000
  11.000   1.3864   0.04626   0.03747  -0.0585   0.0559   1.0000
  11.250   1.2932   0.04006   0.03200  -0.0437   0.0571   1.0000
  11.500   1.3152   0.04366   0.03560  -0.0435   0.0536   1.0000
  11.750   1.4233   0.05683   0.04895  -0.0542   0.0510   1.0000
  12.000   1.4175   0.06003   0.05254  -0.0511   0.0505   1.0000
  12.250   1.4076   0.06336   0.05622  -0.0480   0.0501   1.0000
  12.500   1.3942   0.06690   0.06010  -0.0454   0.0497   1.0000
  12.750   1.3783   0.07075   0.06427  -0.0432   0.0495   1.0000
  13.000   1.3601   0.07501   0.06882  -0.0417   0.0493   1.0000
  13.250   1.3395   0.07970   0.07380  -0.0408   0.0494   1.0000
  13.500   1.3171   0.08494   0.07930  -0.0408   0.0496   1.0000
  13.750   1.2932   0.09072   0.08532  -0.0417   0.0499   1.0000
  14.000   1.2685   0.09711   0.09192  -0.0434   0.0504   1.0000
  14.250   1.2432   0.10410   0.09911  -0.0462   0.0509   1.0000
  14.500   1.2190   0.11164   0.10680  -0.0497   0.0515   1.0000
  14.750   1.1965   0.11967   0.11496  -0.0538   0.0520   1.0000
  15.000   1.1790   0.12778   0.12313  -0.0576   0.0526   1.0000
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