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D.G.A. 1138 (dga1138-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: D.G.A. 1138 (dga1138-il)
Reynolds number: 1,000,000
Max Cl/Cd: 77.02 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dga1138-il-1000000-n5.txt
Download as CSV file: xf-dga1138-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: D.G.A. 1138                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.5590   0.12882   0.12715   0.0008   1.0000   0.0033
 -12.250  -0.5585   0.12406   0.12240  -0.0010   1.0000   0.0035
 -11.250  -0.8658   0.02831   0.02555  -0.0555   1.0000   0.0031
 -11.000  -0.8551   0.02487   0.02178  -0.0546   1.0000   0.0032
 -10.750  -0.8394   0.02266   0.01929  -0.0536   1.0000   0.0033
 -10.500  -0.8212   0.02103   0.01746  -0.0526   1.0000   0.0035
 -10.250  -0.8019   0.01966   0.01591  -0.0516   1.0000   0.0036
 -10.000  -0.7817   0.01847   0.01455  -0.0506   1.0000   0.0038
  -9.750  -0.7577   0.01736   0.01327  -0.0502   0.9995   0.0040
  -9.500  -0.7293   0.01633   0.01206  -0.0508   0.9981   0.0042
  -9.250  -0.6999   0.01544   0.01101  -0.0515   0.9966   0.0044
  -9.000  -0.6697   0.01468   0.01011  -0.0523   0.9952   0.0045
  -8.750  -0.6408   0.01374   0.00903  -0.0529   0.9930   0.0051
  -8.500  -0.6114   0.01305   0.00822  -0.0534   0.9902   0.0056
  -8.250  -0.5809   0.01245   0.00753  -0.0542   0.9875   0.0061
  -8.000  -0.5514   0.01193   0.00690  -0.0546   0.9841   0.0066
  -7.750  -0.5222   0.01142   0.00631  -0.0550   0.9791   0.0073
  -7.500  -0.4925   0.01086   0.00568  -0.0555   0.9738   0.0086
  -7.250  -0.4620   0.01039   0.00515  -0.0561   0.9661   0.0100
  -7.000  -0.4305   0.01006   0.00482  -0.0569   0.9556   0.0138
  -6.750  -0.3982   0.01009   0.00493  -0.0578   0.9426   0.0185
  -6.500  -0.3681   0.01021   0.00502  -0.0581   0.9289   0.0216
  -6.250  -0.3399   0.01024   0.00498  -0.0580   0.9165   0.0234
  -6.000  -0.3120   0.01036   0.00505  -0.0579   0.9067   0.0245
  -5.750  -0.2840   0.01048   0.00512  -0.0578   0.8985   0.0251
  -5.500  -0.2562   0.01051   0.00510  -0.0577   0.8916   0.0254
  -5.250  -0.2293   0.01028   0.00478  -0.0575   0.8824   0.0260
  -5.000  -0.2032   0.00974   0.00415  -0.0571   0.8701   0.0275
  -4.750  -0.1762   0.00952   0.00387  -0.0569   0.8584   0.0282
  -4.500  -0.1491   0.00923   0.00351  -0.0567   0.8492   0.0283
  -4.250  -0.1220   0.00898   0.00318  -0.0564   0.8388   0.0285
  -4.000  -0.0947   0.00879   0.00293  -0.0563   0.8267   0.0290
  -3.750  -0.0674   0.00854   0.00261  -0.0561   0.8150   0.0290
  -3.500  -0.0401   0.00833   0.00233  -0.0559   0.8026   0.0290
  -3.250  -0.0127   0.00815   0.00207  -0.0557   0.7891   0.0292
  -3.000   0.0145   0.00803   0.00186  -0.0555   0.7718   0.0294
  -2.750   0.0416   0.00795   0.00168  -0.0553   0.7512   0.0299
  -2.500   0.0690   0.00789   0.00152  -0.0551   0.7322   0.0306
  -2.250   0.0962   0.00786   0.00141  -0.0550   0.7110   0.0317
  -2.000   0.1232   0.00789   0.00132  -0.0547   0.6779   0.0334
  -1.750   0.1473   0.00832   0.00129  -0.0541   0.5519   0.0346
  -1.500   0.1745   0.00841   0.00128  -0.0540   0.5265   0.0352
  -1.250   0.2020   0.00842   0.00122  -0.0539   0.5112   0.0372
  -1.000   0.2296   0.00842   0.00118  -0.0539   0.4985   0.0395
  -0.750   0.2572   0.00844   0.00116  -0.0539   0.4831   0.0418
  -0.500   0.2849   0.00846   0.00114  -0.0539   0.4682   0.0443
  -0.250   0.3126   0.00850   0.00114  -0.0539   0.4523   0.0465
   0.000   0.3402   0.00851   0.00112  -0.0539   0.4342   0.0548
   0.250   0.3671   0.00847   0.00113  -0.0539   0.4024   0.1136
   0.500   0.3928   0.00872   0.00122  -0.0537   0.3374   0.1392
   0.750   0.4183   0.00900   0.00136  -0.0535   0.2751   0.1704
   1.000   0.4429   0.00943   0.00155  -0.0531   0.1871   0.2103
   1.250   0.4699   0.00948   0.00166  -0.0531   0.1732   0.2499
   1.500   0.4970   0.00948   0.00177  -0.0531   0.1649   0.3005
   2.000   0.5724   0.00810   0.00212  -0.0584   0.1474   1.0000
   2.250   0.5981   0.00824   0.00222  -0.0580   0.1391   1.0000
   2.500   0.6240   0.00836   0.00232  -0.0577   0.1318   1.0000
   2.750   0.6488   0.00866   0.00245  -0.0572   0.0966   1.0000
   3.000   0.6738   0.00891   0.00262  -0.0568   0.0806   1.0000
   3.250   0.6990   0.00914   0.00280  -0.0564   0.0703   1.0000
   3.500   0.7221   0.00969   0.00313  -0.0556   0.0256   1.0000
   3.750   0.7470   0.00998   0.00339  -0.0551   0.0151   1.0000
   4.000   0.7722   0.01024   0.00366  -0.0547   0.0111   1.0000
   4.250   0.7976   0.01048   0.00393  -0.0543   0.0098   1.0000
   4.500   0.8229   0.01073   0.00421  -0.0539   0.0089   1.0000
   4.750   0.8480   0.01101   0.00453  -0.0535   0.0080   1.0000
   5.000   0.8727   0.01136   0.00489  -0.0530   0.0070   1.0000
   5.250   0.8971   0.01176   0.00533  -0.0525   0.0062   1.0000
   5.500   0.9219   0.01209   0.00570  -0.0521   0.0058   1.0000
   5.750   0.9464   0.01247   0.00611  -0.0516   0.0054   1.0000
   6.000   0.9708   0.01286   0.00655  -0.0512   0.0050   1.0000
   6.250   0.9949   0.01327   0.00699  -0.0507   0.0047   1.0000
   6.500   1.0185   0.01376   0.00752  -0.0501   0.0044   1.0000
   6.750   1.0400   0.01457   0.00841  -0.0492   0.0040   1.0000
   7.000   1.0636   0.01503   0.00892  -0.0486   0.0039   1.0000
   7.250   1.0868   0.01553   0.00948  -0.0480   0.0037   1.0000
   7.500   1.1094   0.01608   0.01010  -0.0474   0.0034   1.0000
   7.750   1.1313   0.01673   0.01082  -0.0466   0.0033   1.0000
   8.000   1.1529   0.01739   0.01158  -0.0458   0.0031   1.0000
   8.250   1.1742   0.01806   0.01232  -0.0450   0.0030   1.0000
   8.500   1.1952   0.01874   0.01306  -0.0442   0.0029   1.0000
   8.750   1.2155   0.01946   0.01386  -0.0433   0.0028   1.0000
   9.000   1.2349   0.02028   0.01475  -0.0422   0.0027   1.0000
   9.250   1.2517   0.02137   0.01596  -0.0408   0.0026   1.0000
   9.500   1.2635   0.02304   0.01781  -0.0386   0.0024   1.0000
   9.750   1.2796   0.02410   0.01900  -0.0371   0.0024   1.0000
  10.000   1.2941   0.02527   0.02032  -0.0355   0.0024   1.0000
  10.250   1.3066   0.02659   0.02180  -0.0335   0.0023   1.0000
  10.500   1.3161   0.02812   0.02350  -0.0312   0.0023   1.0000
  10.750   1.3220   0.02980   0.02539  -0.0285   0.0022   1.0000
  11.000   1.3221   0.03155   0.02734  -0.0248   0.0021   1.0000
  11.250   1.3184   0.03359   0.02958  -0.0210   0.0021   1.0000
  11.500   1.3126   0.03596   0.03215  -0.0176   0.0020   1.0000
  11.750   1.3038   0.03879   0.03520  -0.0147   0.0020   1.0000
  12.000   1.2921   0.04213   0.03877  -0.0124   0.0020   1.0000
  12.250   1.2772   0.04616   0.04302  -0.0111   0.0020   1.0000
  12.500   1.2595   0.05105   0.04813  -0.0109   0.0019   1.0000
  12.750   1.2401   0.05680   0.05409  -0.0122   0.0019   1.0000
  13.000   1.2195   0.06368   0.06117  -0.0152   0.0019   1.0000
  13.250   1.1969   0.07221   0.06990  -0.0203   0.0019   1.0000
  13.500   1.1726   0.08175   0.07961  -0.0261   0.0019   1.0000
  13.750   1.1472   0.09233   0.09034  -0.0325   0.0020   1.0000
  14.000   1.1214   0.10379   0.10194  -0.0388   0.0020   1.0000
  14.250   1.0932   0.11590   0.11412  -0.0448   0.0020   1.0000
  14.500   1.0644   0.12784   0.12614  -0.0505   0.0021   1.0000
  14.750   1.0338   0.14054   0.13891  -0.0563   0.0022   1.0000
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