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D.G.A. 1138 (dga1138-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: D.G.A. 1138 (dga1138-il)
Reynolds number: 1,000,000
Max Cl/Cd: 86.59 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dga1138-il-1000000.txt
Download as CSV file: xf-dga1138-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.4065   0.13834   0.13671  -0.0094   1.0000   0.0101
 -13.250  -0.4038   0.13531   0.13368  -0.0104   1.0000   0.0108
 -10.250  -0.7824   0.02526   0.02243  -0.0532   1.0000   0.0082
 -10.000  -0.7676   0.02272   0.01956  -0.0520   1.0000   0.0085
  -9.750  -0.7524   0.02023   0.01670  -0.0508   1.0000   0.0088
  -9.500  -0.7378   0.01750   0.01355  -0.0492   1.0000   0.0096
  -9.250  -0.7159   0.01683   0.01280  -0.0482   1.0000   0.0101
  -9.000  -0.6940   0.01623   0.01211  -0.0471   1.0000   0.0106
  -8.750  -0.6725   0.01554   0.01130  -0.0460   1.0000   0.0112
  -8.500  -0.6516   0.01487   0.01050  -0.0447   1.0000   0.0117
  -8.250  -0.6250   0.01414   0.00961  -0.0446   0.9994   0.0123
  -8.000  -0.5932   0.01334   0.00871  -0.0456   0.9982   0.0138
  -7.750  -0.5592   0.01337   0.00875  -0.0469   0.9969   0.0149
  -7.500  -0.5251   0.01334   0.00869  -0.0483   0.9956   0.0161
  -7.250  -0.4919   0.01278   0.00803  -0.0496   0.9945   0.0174
  -7.000  -0.4588   0.01295   0.00824  -0.0507   0.9925   0.0186
  -6.750  -0.4256   0.01320   0.00850  -0.0518   0.9902   0.0197
  -6.500  -0.3923   0.01315   0.00840  -0.0529   0.9880   0.0211
  -6.250  -0.3585   0.01318   0.00839  -0.0542   0.9861   0.0222
  -6.000  -0.3261   0.01220   0.00728  -0.0554   0.9844   0.0240
  -5.750  -0.2943   0.01202   0.00709  -0.0564   0.9808   0.0252
  -5.500  -0.2634   0.01185   0.00688  -0.0570   0.9753   0.0264
  -5.000  -0.1999   0.01135   0.00630  -0.0586   0.9606   0.0292
  -4.750  -0.1689   0.01103   0.00590  -0.0592   0.9508   0.0301
  -4.500  -0.1387   0.01111   0.00593  -0.0596   0.9399   0.0308
  -4.250  -0.1121   0.00991   0.00460  -0.0593   0.9282   0.0319
  -4.000  -0.0860   0.00917   0.00380  -0.0588   0.9170   0.0334
  -3.750  -0.0591   0.00889   0.00349  -0.0585   0.9070   0.0347
  -3.500  -0.0323   0.00865   0.00319  -0.0582   0.8970   0.0358
  -3.250  -0.0053   0.00842   0.00290  -0.0579   0.8878   0.0366
  -3.000   0.0220   0.00818   0.00262  -0.0577   0.8793   0.0373
  -2.750   0.0492   0.00797   0.00237  -0.0575   0.8713   0.0379
  -2.500   0.0767   0.00778   0.00214  -0.0573   0.8623   0.0385
  -2.250   0.1043   0.00761   0.00194  -0.0571   0.8537   0.0394
  -2.000   0.1318   0.00750   0.00179  -0.0569   0.8440   0.0406
  -1.750   0.1595   0.00741   0.00167  -0.0568   0.8323   0.0416
  -1.500   0.1866   0.00724   0.00143  -0.0566   0.8167   0.0440
  -1.250   0.2137   0.00714   0.00126  -0.0563   0.7958   0.0470
  -1.000   0.2405   0.00712   0.00113  -0.0559   0.7699   0.0500
  -0.750   0.2673   0.00715   0.00104  -0.0556   0.7433   0.0534
  -0.500   0.2937   0.00696   0.00100  -0.0554   0.7175   0.1337
  -0.250   0.3202   0.00692   0.00102  -0.0552   0.6864   0.1856
   0.000   0.3445   0.00719   0.00105  -0.0545   0.5833   0.2267
   0.250   0.3698   0.00736   0.00116  -0.0542   0.5333   0.2849
   0.500   0.3871   0.00589   0.00125  -0.0526   0.5170   0.8372
   0.750   0.4501   0.00589   0.00146  -0.0605   0.4969   0.9993
   1.000   0.4792   0.00601   0.00151  -0.0609   0.4812   1.0000
   1.250   0.5054   0.00612   0.00156  -0.0605   0.4647   1.0000
   1.500   0.5314   0.00624   0.00161  -0.0602   0.4441   1.0000
   1.750   0.5568   0.00643   0.00166  -0.0598   0.4036   1.0000
   2.000   0.5779   0.00721   0.00188  -0.0587   0.2758   1.0000
   2.250   0.6001   0.00787   0.00213  -0.0579   0.1867   1.0000
   2.500   0.6255   0.00809   0.00228  -0.0575   0.1715   1.0000
   2.750   0.6510   0.00827   0.00241  -0.0571   0.1621   1.0000
   3.000   0.6769   0.00842   0.00255  -0.0568   0.1540   1.0000
   3.250   0.7024   0.00861   0.00268  -0.0564   0.1416   1.0000
   3.500   0.7279   0.00880   0.00283  -0.0560   0.1252   1.0000
   3.750   0.7515   0.00927   0.00305  -0.0554   0.0815   1.0000
   4.000   0.7732   0.01003   0.00349  -0.0544   0.0237   1.0000
   4.250   0.7979   0.01039   0.00385  -0.0538   0.0168   1.0000
   4.500   0.8230   0.01069   0.00420  -0.0534   0.0154   1.0000
   4.750   0.8477   0.01105   0.00460  -0.0529   0.0140   1.0000
   5.000   0.8718   0.01152   0.00512  -0.0522   0.0128   1.0000
   5.250   0.8941   0.01229   0.00601  -0.0512   0.0116   1.0000
   5.500   0.9192   0.01258   0.00632  -0.0508   0.0110   1.0000
   5.750   0.9432   0.01304   0.00683  -0.0502   0.0104   1.0000
   6.000   0.9666   0.01359   0.00743  -0.0495   0.0098   1.0000
   6.250   0.9896   0.01418   0.00807  -0.0487   0.0094   1.0000
   6.500   1.0121   0.01482   0.00875  -0.0480   0.0089   1.0000
   6.750   1.0334   0.01562   0.00960  -0.0470   0.0085   1.0000
   7.000   1.0486   0.01737   0.01147  -0.0450   0.0080   1.0000
   7.250   1.0680   0.01862   0.01281  -0.0437   0.0077   1.0000
   7.500   1.0902   0.01932   0.01360  -0.0429   0.0075   1.0000
   7.750   1.1115   0.02019   0.01456  -0.0419   0.0072   1.0000
   8.000   1.1322   0.02111   0.01558  -0.0409   0.0069   1.0000
   8.250   1.1518   0.02224   0.01682  -0.0398   0.0066   1.0000
   8.500   1.1699   0.02367   0.01840  -0.0384   0.0065   1.0000
   8.750   1.1869   0.02526   0.02016  -0.0369   0.0064   1.0000
   9.000   1.2026   0.02695   0.02202  -0.0353   0.0063   1.0000
   9.250   1.2163   0.02886   0.02413  -0.0335   0.0062   1.0000
   9.500   1.2285   0.03069   0.02614  -0.0315   0.0061   1.0000
   9.750   1.2389   0.03254   0.02817  -0.0294   0.0060   1.0000
  10.000   1.2475   0.03435   0.03014  -0.0272   0.0059   1.0000
  10.250   1.2558   0.03586   0.03177  -0.0251   0.0058   1.0000
  10.500   1.2586   0.03771   0.03379  -0.0223   0.0057   1.0000
  10.750   1.2551   0.03955   0.03577  -0.0186   0.0056   1.0000
  11.000   1.2489   0.04161   0.03796  -0.0150   0.0055   1.0000
  11.250   1.2378   0.04439   0.04093  -0.0118   0.0055   1.0000
  11.500   1.2251   0.04758   0.04430  -0.0095   0.0054   1.0000
  11.750   1.2092   0.05147   0.04838  -0.0080   0.0054   1.0000
  12.000   1.1922   0.05595   0.05305  -0.0078   0.0054   1.0000
  12.250   1.1740   0.06120   0.05847  -0.0089   0.0054   1.0000
  12.500   1.1558   0.06719   0.06464  -0.0114   0.0054   1.0000
  12.750   1.1371   0.07440   0.07203  -0.0158   0.0054   1.0000
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