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D.G.A. 1138 (dga1138-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: D.G.A. 1138 (dga1138-il)
Reynolds number: 200,000
Max Cl/Cd: 69.27 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dga1138-il-200000.txt
Download as CSV file: xf-dga1138-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4919   0.10302   0.09943  -0.0179   1.0000   0.0412
  -9.500  -0.4938   0.09948   0.09594  -0.0219   1.0000   0.0415
  -9.250  -0.4964   0.09581   0.09232  -0.0254   1.0000   0.0417
  -9.000  -0.4939   0.09146   0.08799  -0.0298   1.0000   0.0418
  -8.750  -0.4976   0.08489   0.08147  -0.0312   1.0000   0.0424
  -8.500  -0.4927   0.08179   0.07838  -0.0280   1.0000   0.0434
  -8.250  -0.4864   0.07886   0.07546  -0.0275   1.0000   0.0446
  -8.000  -0.4805   0.07557   0.07218  -0.0285   1.0000   0.0459
  -7.750  -0.4746   0.07188   0.06848  -0.0302   1.0000   0.0475
  -7.500  -0.4676   0.06769   0.06426  -0.0328   1.0000   0.0498
  -7.250  -0.4509   0.06085   0.05707  -0.0415   1.0000   0.0538
  -7.000  -0.4501   0.05462   0.05081  -0.0415   1.0000   0.0551
  -6.750  -0.4418   0.05378   0.05007  -0.0385   1.0000   0.0573
  -6.500  -0.4309   0.05160   0.04783  -0.0376   1.0000   0.0619
  -6.250  -0.4204   0.04639   0.04235  -0.0388   1.0000   0.0689
  -6.000  -0.4091   0.04517   0.04114  -0.0368   1.0000   0.0730
  -5.750  -0.3967   0.04221   0.03800  -0.0362   1.0000   0.0825
  -5.500  -0.3828   0.04008   0.03570  -0.0354   1.0000   0.0941
  -5.250  -0.3682   0.03856   0.03405  -0.0342   1.0000   0.1069
  -4.750  -0.3181   0.02312   0.01657  -0.0334   1.0000   0.0639
  -4.500  -0.2948   0.02131   0.01431  -0.0325   1.0000   0.0647
  -4.250  -0.2700   0.01963   0.01229  -0.0318   1.0000   0.0642
  -4.000  -0.2438   0.01840   0.01078  -0.0314   1.0000   0.0641
  -3.750  -0.2141   0.01766   0.00980  -0.0317   0.9990   0.0659
  -3.500  -0.1775   0.01680   0.00877  -0.0334   0.9966   0.0665
  -3.250  -0.1405   0.01574   0.00764  -0.0352   0.9946   0.0674
  -3.000  -0.1042   0.01494   0.00685  -0.0371   0.9912   0.0690
  -2.750  -0.0672   0.01441   0.00635  -0.0391   0.9875   0.0722
  -2.500  -0.0285   0.01404   0.00597  -0.0415   0.9844   0.0762
  -2.250   0.0081   0.01370   0.00561  -0.0433   0.9791   0.0797
  -2.000   0.0480   0.01332   0.00532  -0.0458   0.9739   0.0906
  -1.750   0.0891   0.01286   0.00516  -0.0487   0.9693   0.1602
  -1.500   0.1260   0.01255   0.00505  -0.0506   0.9620   0.2191
  -1.250   0.1696   0.01213   0.00488  -0.0540   0.9578   0.2816
  -1.000   0.2259   0.01015   0.00501  -0.0599   0.9585   0.9997
  -0.750   0.2647   0.01004   0.00478  -0.0621   0.9510   1.0000
  -0.500   0.3078   0.00985   0.00449  -0.0651   0.9451   1.0000
  -0.250   0.3428   0.00973   0.00432  -0.0664   0.9361   1.0000
   0.000   0.3820   0.00955   0.00410  -0.0686   0.9298   1.0000
   0.250   0.4128   0.00947   0.00399  -0.0689   0.9186   1.0000
   0.500   0.4436   0.00936   0.00386  -0.0690   0.9058   1.0000
   0.750   0.4720   0.00927   0.00374  -0.0686   0.8906   1.0000
   1.000   0.4986   0.00919   0.00363  -0.0677   0.8728   1.0000
   1.250   0.5218   0.00916   0.00356  -0.0661   0.8485   1.0000
   1.500   0.5455   0.00912   0.00348  -0.0646   0.8214   1.0000
   1.750   0.5696   0.00911   0.00341  -0.0633   0.7924   1.0000
   2.000   0.5944   0.00916   0.00340  -0.0622   0.7651   1.0000
   2.250   0.6192   0.00926   0.00342  -0.0612   0.7341   1.0000
   2.500   0.6436   0.00942   0.00350  -0.0601   0.6973   1.0000
   2.750   0.6671   0.00963   0.00358  -0.0590   0.6452   1.0000
   3.000   0.6887   0.01002   0.00365  -0.0574   0.5771   1.0000
   3.250   0.7099   0.01059   0.00390  -0.0560   0.5285   1.0000
   3.500   0.7316   0.01116   0.00427  -0.0547   0.4744   1.0000
   3.750   0.7515   0.01179   0.00451  -0.0533   0.3624   1.0000
   4.000   0.7683   0.01295   0.00500  -0.0517   0.2500   1.0000
   4.250   0.7900   0.01365   0.00549  -0.0509   0.2112   1.0000
   4.500   0.8127   0.01424   0.00598  -0.0501   0.1890   1.0000
   4.750   0.8356   0.01479   0.00648  -0.0495   0.1630   1.0000
   5.000   0.8598   0.01521   0.00684  -0.0489   0.1298   1.0000
   5.250   0.8801   0.01623   0.00744  -0.0478   0.0577   1.0000
   5.500   0.9007   0.01727   0.00832  -0.0465   0.0385   1.0000
   5.750   0.9211   0.01832   0.00940  -0.0452   0.0327   1.0000
   6.000   0.9422   0.01923   0.01049  -0.0439   0.0308   1.0000
   6.250   0.9620   0.02031   0.01169  -0.0425   0.0293   1.0000
   6.500   0.9811   0.02155   0.01302  -0.0410   0.0282   1.0000
   6.750   1.0003   0.02296   0.01451  -0.0395   0.0275   1.0000
   7.000   1.0201   0.02453   0.01617  -0.0381   0.0266   1.0000
   7.250   1.0393   0.02669   0.01842  -0.0369   0.0251   1.0000
   7.500   1.0596   0.02980   0.02173  -0.0358   0.0244   1.0000
   7.750   1.0799   0.03225   0.02445  -0.0346   0.0245   1.0000
   8.000   1.0990   0.03442   0.02690  -0.0332   0.0247   1.0000
   8.250   1.1168   0.03637   0.02920  -0.0315   0.0253   1.0000
   8.500   1.1246   0.04079   0.03449  -0.0278   0.0282   1.0000
   8.750   1.1234   0.04653   0.04083  -0.0243   0.0310   1.0000
   9.250   1.0225   0.04970   0.04537  -0.0075   0.0400   1.0000
  14.000   0.8789   0.18572   0.18206  -0.0676   0.0483   1.0000
  14.250   0.8849   0.18934   0.18569  -0.0690   0.0463   1.0000
  14.500   0.8961   0.19212   0.18849  -0.0687   0.0444   1.0000
  14.750   0.6746   0.17161   0.16824  -0.0397   0.0531   1.0000
  15.000   0.6590   0.17379   0.17040  -0.0438   0.0510   1.0000
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