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DAE-51 AIRFOIL (dae51-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: DAE-51 AIRFOIL (dae51-il)
Reynolds number: 1,000,000
Max Cl/Cd: 127.18 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dae51-il-1000000-n5.txt
Download as CSV file: xf-dae51-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4030   0.11085   0.10918  -0.0226   0.9716   0.0062
  -8.000  -0.4269   0.01973   0.01600  -0.0956   0.8436   0.0073
  -7.750  -0.4024   0.01763   0.01353  -0.0962   0.8380   0.0075
  -7.500  -0.3764   0.01613   0.01177  -0.0967   0.8325   0.0077
  -7.250  -0.3498   0.01500   0.01040  -0.0969   0.8269   0.0079
  -7.000  -0.3229   0.01409   0.00930  -0.0972   0.8218   0.0081
  -6.750  -0.2954   0.01335   0.00840  -0.0974   0.8163   0.0083
  -6.500  -0.2678   0.01274   0.00764  -0.0975   0.8109   0.0084
  -6.250  -0.2400   0.01219   0.00696  -0.0977   0.8059   0.0085
  -6.000  -0.2121   0.01157   0.00622  -0.0979   0.8005   0.0087
  -5.750  -0.1843   0.01089   0.00541  -0.0981   0.7951   0.0090
  -5.500  -0.1561   0.01046   0.00490  -0.0982   0.7901   0.0092
  -5.250  -0.1277   0.01011   0.00449  -0.0984   0.7845   0.0094
  -4.750  -0.0709   0.00951   0.00376  -0.0987   0.7738   0.0100
  -4.500  -0.0423   0.00925   0.00344  -0.0989   0.7679   0.0105
  -4.250  -0.0138   0.00903   0.00316  -0.0990   0.7627   0.0110
  -4.000   0.0149   0.00881   0.00290  -0.0992   0.7567   0.0114
  -3.750   0.0436   0.00854   0.00255  -0.0994   0.7507   0.0120
  -3.500   0.0723   0.00831   0.00230  -0.0995   0.7449   0.0129
  -3.250   0.1011   0.00815   0.00210  -0.0997   0.7383   0.0137
  -3.000   0.1298   0.00801   0.00192  -0.0999   0.7322   0.0148
  -2.750   0.1586   0.00787   0.00174  -0.1000   0.7251   0.0160
  -2.500   0.1873   0.00774   0.00159  -0.1002   0.7186   0.0180
  -2.250   0.2162   0.00764   0.00147  -0.1003   0.7113   0.0201
  -2.000   0.2449   0.00753   0.00135  -0.1005   0.7042   0.0250
  -1.750   0.2737   0.00743   0.00125  -0.1007   0.6962   0.0318
  -1.500   0.3024   0.00734   0.00117  -0.1009   0.6883   0.0431
  -1.250   0.3311   0.00724   0.00110  -0.1011   0.6795   0.0611
  -1.000   0.3598   0.00713   0.00104  -0.1013   0.6709   0.0866
  -0.750   0.3884   0.00700   0.00099  -0.1015   0.6614   0.1328
  -0.500   0.4171   0.00679   0.00097  -0.1018   0.6512   0.2046
  -0.250   0.4457   0.00662   0.00096  -0.1021   0.6408   0.2804
   0.000   0.4741   0.00648   0.00097  -0.1024   0.6295   0.3551
   0.250   0.5025   0.00637   0.00099  -0.1026   0.6176   0.4234
   0.500   0.5308   0.00620   0.00104  -0.1028   0.6051   0.5232
   0.750   0.5589   0.00608   0.00110  -0.1030   0.5925   0.6078
   1.000   0.5868   0.00599   0.00116  -0.1031   0.5796   0.6858
   1.250   0.6140   0.00587   0.00124  -0.1029   0.5667   0.7720
   1.500   0.6380   0.00568   0.00131  -0.1020   0.5539   0.8826
   1.750   0.6652   0.00561   0.00132  -0.1017   0.5404   1.0000
   2.000   0.6933   0.00575   0.00138  -0.1018   0.5264   1.0000
   2.250   0.7214   0.00589   0.00145  -0.1018   0.5118   1.0000
   2.500   0.7493   0.00604   0.00153  -0.1019   0.4968   1.0000
   2.750   0.7771   0.00620   0.00162  -0.1020   0.4810   1.0000
   3.000   0.8048   0.00637   0.00172  -0.1020   0.4643   1.0000
   3.250   0.8324   0.00655   0.00183  -0.1020   0.4471   1.0000
   3.500   0.8597   0.00676   0.00196  -0.1020   0.4286   1.0000
   3.750   0.8869   0.00698   0.00209  -0.1020   0.4089   1.0000
   4.000   0.9137   0.00723   0.00226  -0.1019   0.3855   1.0000
   4.250   0.9403   0.00751   0.00243  -0.1018   0.3615   1.0000
   4.500   0.9664   0.00784   0.00263  -0.1017   0.3330   1.0000
   4.750   0.9914   0.00830   0.00290  -0.1014   0.2943   1.0000
   5.000   1.0170   0.00868   0.00315  -0.1012   0.2658   1.0000
   5.250   1.0421   0.00909   0.00342  -0.1009   0.2356   1.0000
   5.500   1.0657   0.00968   0.00378  -0.1004   0.1924   1.0000
   5.750   1.0900   0.01016   0.00411  -0.1000   0.1627   1.0000
   6.000   1.1145   0.01061   0.00444  -0.0996   0.1387   1.0000
   6.250   1.1383   0.01112   0.00481  -0.0992   0.1128   1.0000
   6.500   1.1622   0.01160   0.00518  -0.0987   0.0914   1.0000
   6.750   1.1859   0.01208   0.00558  -0.0982   0.0736   1.0000
   7.000   1.2093   0.01258   0.00598  -0.0977   0.0570   1.0000
   7.250   1.2324   0.01308   0.00641  -0.0971   0.0440   1.0000
   7.500   1.2557   0.01355   0.00684  -0.0966   0.0348   1.0000
   7.750   1.2791   0.01398   0.00725  -0.0960   0.0285   1.0000
   8.000   1.3022   0.01442   0.00767  -0.0954   0.0238   1.0000
   8.250   1.3248   0.01490   0.00813  -0.0948   0.0200   1.0000
   8.500   1.3476   0.01531   0.00856  -0.0941   0.0177   1.0000
   8.750   1.3694   0.01581   0.00906  -0.0934   0.0155   1.0000
   9.000   1.3915   0.01626   0.00954  -0.0926   0.0142   1.0000
   9.250   1.4130   0.01672   0.01003  -0.0918   0.0131   1.0000
   9.500   1.4335   0.01726   0.01058  -0.0909   0.0120   1.0000
   9.750   1.4530   0.01783   0.01120  -0.0898   0.0110   1.0000
  10.000   1.4731   0.01832   0.01174  -0.0888   0.0105   1.0000
  10.250   1.4920   0.01887   0.01232  -0.0876   0.0097   1.0000
  10.500   1.5093   0.01947   0.01295  -0.0862   0.0091   1.0000
  10.750   1.5232   0.02013   0.01365  -0.0842   0.0085   1.0000
  11.000   1.5364   0.02087   0.01444  -0.0822   0.0080   1.0000
  11.250   1.5505   0.02157   0.01521  -0.0805   0.0077   1.0000
  11.500   1.5639   0.02234   0.01604  -0.0788   0.0074   1.0000
  11.750   1.5765   0.02318   0.01695  -0.0770   0.0071   1.0000
  12.000   1.5885   0.02411   0.01794  -0.0753   0.0068   1.0000
  12.250   1.5997   0.02512   0.01901  -0.0737   0.0065   1.0000
  12.500   1.6099   0.02623   0.02018  -0.0720   0.0063   1.0000
  12.750   1.6189   0.02749   0.02150  -0.0704   0.0060   1.0000
  13.000   1.6254   0.02899   0.02310  -0.0686   0.0057   1.0000
  13.250   1.6336   0.03039   0.02458  -0.0671   0.0055   1.0000
  13.500   1.6419   0.03182   0.02609  -0.0657   0.0054   1.0000
  13.750   1.6491   0.03337   0.02773  -0.0644   0.0053   1.0000
  14.000   1.6552   0.03508   0.02952  -0.0631   0.0052   1.0000
  14.250   1.6602   0.03693   0.03146  -0.0619   0.0050   1.0000
  14.500   1.6642   0.03891   0.03354  -0.0608   0.0049   1.0000
  14.750   1.6675   0.04103   0.03575  -0.0598   0.0048   1.0000
  15.000   1.6696   0.04335   0.03816  -0.0589   0.0047   1.0000
  15.250   1.6705   0.04581   0.04072  -0.0580   0.0046   1.0000
  15.500   1.6707   0.04845   0.04346  -0.0574   0.0045   1.0000
  15.750   1.6696   0.05133   0.04644  -0.0569   0.0044   1.0000
  16.000   1.6677   0.05441   0.04963  -0.0566   0.0043   1.0000
  16.250   1.6645   0.05776   0.05308  -0.0565   0.0042   1.0000
  16.500   1.6600   0.06144   0.05687  -0.0566   0.0042   1.0000
  16.750   1.6541   0.06542   0.06096  -0.0570   0.0041   1.0000
  17.000   1.6461   0.06979   0.06545  -0.0576   0.0040   1.0000
  17.250   1.6364   0.07454   0.07032  -0.0584   0.0040   1.0000
  17.500   1.6252   0.07968   0.07559  -0.0596   0.0039   1.0000
  17.750   1.6118   0.08529   0.08133  -0.0611   0.0039   1.0000
  18.000   1.5965   0.09133   0.08750  -0.0629   0.0038   1.0000
  18.250   1.5802   0.09770   0.09401  -0.0651   0.0038   1.0000
  18.500   1.5634   0.10433   0.10077  -0.0675   0.0038   1.0000
  18.750   1.5458   0.11120   0.10777  -0.0701   0.0037   1.0000
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