Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

D.G.A. 1138 (dga1138-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: D.G.A. 1138 (dga1138-il)
Reynolds number: 500,000
Max Cl/Cd: 79.82 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dga1138-il-500000.txt
Download as CSV file: xf-dga1138-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3948   0.08469   0.08253  -0.0268   1.0000   0.0226
  -9.500  -0.3975   0.08020   0.07806  -0.0281   1.0000   0.0227
  -9.250  -0.4014   0.07571   0.07359  -0.0294   1.0000   0.0227
  -9.000  -0.4076   0.07122   0.06912  -0.0307   1.0000   0.0227
  -8.750  -0.4178   0.06707   0.06501  -0.0316   1.0000   0.0227
  -8.500  -0.4292   0.06285   0.06082  -0.0328   1.0000   0.0227
  -8.250  -0.4352   0.05781   0.05578  -0.0348   1.0000   0.0227
  -7.500  -0.4822   0.05324   0.05085  -0.0396   1.0000   0.0218
  -7.250  -0.4789   0.04650   0.04395  -0.0406   1.0000   0.0214
  -7.000  -0.4669   0.04895   0.04648  -0.0379   1.0000   0.0256
  -6.750  -0.4520   0.04418   0.04155  -0.0391   0.9992   0.0270
  -6.500  -0.4324   0.02178   0.01700  -0.0443   0.9957   0.0235
  -6.250  -0.3992   0.02138   0.01664  -0.0462   0.9941   0.0251
  -6.000  -0.3670   0.02085   0.01604  -0.0474   0.9914   0.0275
  -5.750  -0.3341   0.01960   0.01445  -0.0484   0.9887   0.0297
  -5.500  -0.3022   0.01754   0.01197  -0.0496   0.9865   0.0322
  -5.250  -0.2693   0.01650   0.01094  -0.0513   0.9848   0.0350
  -5.000  -0.2351   0.01556   0.00985  -0.0527   0.9830   0.0371
  -4.750  -0.2037   0.01474   0.00887  -0.0534   0.9785   0.0389
  -4.500  -0.1692   0.01431   0.00831  -0.0547   0.9755   0.0407
  -4.250  -0.1331   0.01380   0.00768  -0.0563   0.9730   0.0415
  -4.000  -0.0977   0.01253   0.00627  -0.0579   0.9707   0.0426
  -3.750  -0.0690   0.01135   0.00508  -0.0581   0.9640   0.0445
  -3.500  -0.0364   0.01069   0.00442  -0.0591   0.9596   0.0457
  -3.250  -0.0052   0.01019   0.00390  -0.0597   0.9528   0.0467
  -3.000   0.0266   0.00975   0.00343  -0.0604   0.9451   0.0476
  -2.750   0.0561   0.00940   0.00305  -0.0606   0.9360   0.0486
  -2.500   0.0857   0.00910   0.00273  -0.0608   0.9283   0.0502
  -2.250   0.1137   0.00887   0.00246  -0.0607   0.9188   0.0520
  -2.000   0.1413   0.00869   0.00223  -0.0604   0.9097   0.0534
  -1.750   0.1689   0.00854   0.00201  -0.0602   0.9010   0.0558
  -1.500   0.1959   0.00840   0.00185  -0.0598   0.8914   0.0604
  -1.250   0.2228   0.00825   0.00172  -0.0595   0.8812   0.0722
  -1.000   0.2490   0.00796   0.00171  -0.0591   0.8706   0.1620
  -0.750   0.2757   0.00780   0.00172  -0.0588   0.8597   0.2148
  -0.500   0.3021   0.00763   0.00171  -0.0585   0.8465   0.2702
  -0.250   0.3264   0.00708   0.00167  -0.0579   0.8288   0.4537
   0.000   0.3844   0.00580   0.00178  -0.0645   0.8033   1.0000
   0.250   0.4096   0.00588   0.00172  -0.0637   0.7756   1.0000
   0.500   0.4350   0.00598   0.00170  -0.0631   0.7490   1.0000
   0.750   0.4603   0.00610   0.00169  -0.0624   0.7220   1.0000
   1.000   0.4852   0.00627   0.00170  -0.0617   0.6853   1.0000
   1.250   0.5084   0.00657   0.00171  -0.0606   0.6076   1.0000
   1.500   0.5308   0.00702   0.00182  -0.0596   0.5464   1.0000
   1.750   0.5557   0.00728   0.00196  -0.0590   0.5229   1.0000
   2.000   0.5809   0.00750   0.00209  -0.0585   0.5038   1.0000
   2.250   0.6063   0.00770   0.00223  -0.0580   0.4847   1.0000
   2.500   0.6314   0.00791   0.00237  -0.0575   0.4509   1.0000
   2.750   0.6528   0.00856   0.00251  -0.0565   0.3326   1.0000
   3.000   0.6729   0.00948   0.00288  -0.0554   0.2190   1.0000
   3.250   0.6969   0.00991   0.00314  -0.0549   0.1889   1.0000
   3.500   0.7215   0.01024   0.00341  -0.0544   0.1718   1.0000
   3.750   0.7465   0.01054   0.00366  -0.0540   0.1573   1.0000
   4.000   0.7718   0.01079   0.00388  -0.0536   0.1402   1.0000
   4.250   0.7957   0.01125   0.00408  -0.0531   0.0922   1.0000
   4.500   0.8165   0.01217   0.00465  -0.0521   0.0311   1.0000
   4.750   0.8402   0.01271   0.00519  -0.0513   0.0224   1.0000
   5.000   0.8641   0.01322   0.00577  -0.0506   0.0199   1.0000
   5.250   0.8872   0.01388   0.00651  -0.0497   0.0181   1.0000
   5.500   0.9083   0.01481   0.00757  -0.0485   0.0169   1.0000
   5.750   0.9309   0.01547   0.00833  -0.0476   0.0164   1.0000
   6.000   0.9532   0.01618   0.00910  -0.0466   0.0155   1.0000
   6.250   0.9747   0.01697   0.00995  -0.0456   0.0145   1.0000
   6.500   0.9953   0.01793   0.01098  -0.0444   0.0140   1.0000
   6.750   1.0156   0.01898   0.01211  -0.0432   0.0135   1.0000
   7.000   1.0353   0.02018   0.01338  -0.0420   0.0131   1.0000
   7.250   1.0547   0.02160   0.01491  -0.0407   0.0127   1.0000
   7.500   1.0740   0.02334   0.01675  -0.0394   0.0125   1.0000
   7.750   1.0940   0.02508   0.01865  -0.0381   0.0125   1.0000
   8.000   1.1134   0.02765   0.02164  -0.0362   0.0138   1.0000
   8.250   1.1280   0.03088   0.02529  -0.0340   0.0147   1.0000
   8.500   1.1381   0.03449   0.02929  -0.0315   0.0156   1.0000
   8.750   1.1441   0.03999   0.03549  -0.0273   0.0209   1.0000
   9.000   1.1508   0.04236   0.03809  -0.0249   0.0200   1.0000
   9.250   1.1555   0.04478   0.04071  -0.0226   0.0193   1.0000
   9.500   1.1612   0.04722   0.04323  -0.0207   0.0186   1.0000
   9.750   1.1618   0.05037   0.04648  -0.0185   0.0181   1.0000
  10.000   1.1483   0.05494   0.05125  -0.0153   0.0176   1.0000
  10.250   1.1205   0.05965   0.05618  -0.0107   0.0174   1.0000
  10.500   1.0920   0.06425   0.06099  -0.0076   0.0172   1.0000
  10.750   1.0672   0.06886   0.06579  -0.0065   0.0172   1.0000
  11.000   1.0453   0.07373   0.07083  -0.0071   0.0172   1.0000
  11.250   1.0295   0.07843   0.07566  -0.0090   0.0172   1.0000
  11.500   1.0161   0.08354   0.08090  -0.0121   0.0173   1.0000
  11.750   1.0045   0.08934   0.08682  -0.0166   0.0174   1.0000
  12.000   0.9919   0.09680   0.09444  -0.0233   0.0177   1.0000
<< Back to D.G.A. 1138 (dga1138-il)

Polar data table (+)

Polar graphs


<< Back to D.G.A. 1138 (dga1138-il)