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D.G.A. 1138 (dga1138-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: D.G.A. 1138 (dga1138-il)
Reynolds number: 100,000
Max Cl/Cd: 54.54 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dga1138-il-100000.txt
Download as CSV file: xf-dga1138-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4823   0.10431   0.09928  -0.0131   1.0000   0.0869
  -9.250  -0.4919   0.10200   0.09707  -0.0176   1.0000   0.0903
  -9.000  -0.5058   0.09965   0.09482  -0.0248   1.0000   0.0911
  -8.750  -0.4783   0.09463   0.08975  -0.0164   1.0000   0.0997
  -8.500  -0.4886   0.09209   0.08730  -0.0223   1.0000   0.1034
  -8.250  -0.4875   0.08765   0.08290  -0.0247   1.0000   0.1060
  -8.000  -0.4749   0.08455   0.07979  -0.0209   1.0000   0.1117
  -7.750  -0.4807   0.08211   0.07723  -0.0352   1.0000   0.1182
  -7.500  -0.4682   0.07713   0.07241  -0.0262   1.0000   0.1216
  -7.250  -0.4635   0.07518   0.07020  -0.0360   1.0000   0.1322
  -7.000  -0.4544   0.07015   0.06540  -0.0293   1.0000   0.1351
  -6.750  -0.4443   0.06740   0.06243  -0.0346   1.0000   0.1469
  -6.500  -0.4360   0.06391   0.05914  -0.0288   1.0000   0.1521
  -6.250  -0.4254   0.06050   0.05562  -0.0309   1.0000   0.1633
  -6.000  -0.4140   0.05766   0.05277  -0.0296   1.0000   0.1707
  -5.750  -0.4015   0.05412   0.04910  -0.0306   1.0000   0.1786
  -5.500  -0.3855   0.05137   0.04608  -0.0320   1.0000   0.1909
  -5.250  -0.3741   0.04823   0.04302  -0.0297   1.0000   0.1953
  -5.000  -0.3302   0.03460   0.02737  -0.0373   1.0000   0.1045
  -4.750  -0.3114   0.03117   0.02391  -0.0364   1.0000   0.1006
  -4.500  -0.2860   0.02647   0.01820  -0.0359   1.0000   0.0930
  -4.250  -0.2644   0.02526   0.01694  -0.0350   1.0000   0.0968
  -4.000  -0.2394   0.02327   0.01449  -0.0343   1.0000   0.0967
  -3.750  -0.2137   0.02168   0.01254  -0.0336   1.0000   0.0968
  -3.500  -0.1882   0.02051   0.01113  -0.0330   1.0000   0.0982
  -3.250  -0.1627   0.01969   0.01011  -0.0324   1.0000   0.1018
  -3.000  -0.1370   0.01894   0.00929  -0.0320   1.0000   0.1066
  -2.750  -0.1115   0.01832   0.00869  -0.0316   1.0000   0.1106
  -2.500  -0.0861   0.01781   0.00814  -0.0311   1.0000   0.1164
  -2.250  -0.0610   0.01737   0.00776  -0.0307   1.0000   0.1257
  -2.000  -0.0356   0.01700   0.00750  -0.0303   1.0000   0.1468
  -1.750  -0.0097   0.01657   0.00746  -0.0302   1.0000   0.2239
  -1.500   0.0155   0.01637   0.00750  -0.0301   1.0000   0.3035
  -1.250   0.0422   0.01604   0.00751  -0.0304   1.0000   0.3850
  -1.000   0.0737   0.01463   0.00763  -0.0309   1.0000   1.0000
  -0.750   0.0956   0.01494   0.00775  -0.0303   1.0000   1.0000
  -0.500   0.1172   0.01529   0.00795  -0.0297   1.0000   1.0000
  -0.250   0.1387   0.01567   0.00820  -0.0292   1.0000   1.0000
   0.000   0.1723   0.01607   0.00848  -0.0311   0.9961   1.0000
   0.250   0.2275   0.01639   0.00870  -0.0372   0.9848   1.0000
   0.500   0.2803   0.01657   0.00884  -0.0426   0.9725   1.0000
   0.750   0.3309   0.01665   0.00890  -0.0475   0.9596   1.0000
   1.000   0.3814   0.01660   0.00888  -0.0521   0.9461   1.0000
   1.250   0.4338   0.01638   0.00873  -0.0568   0.9321   1.0000
   1.500   0.4891   0.01596   0.00840  -0.0618   0.9177   1.0000
   1.750   0.5389   0.01548   0.00804  -0.0653   0.9024   1.0000
   2.000   0.5777   0.01507   0.00774  -0.0664   0.8817   1.0000
   2.250   0.6141   0.01464   0.00740  -0.0667   0.8599   1.0000
   2.500   0.6420   0.01436   0.00722  -0.0655   0.8332   1.0000
   2.750   0.6683   0.01409   0.00701  -0.0639   0.8036   1.0000
   3.000   0.6938   0.01390   0.00686  -0.0622   0.7712   1.0000
   3.250   0.7181   0.01381   0.00676  -0.0604   0.7315   1.0000
   3.500   0.7410   0.01384   0.00678  -0.0584   0.6820   1.0000
   3.750   0.7630   0.01399   0.00683  -0.0563   0.6184   1.0000
   4.000   0.7831   0.01453   0.00691  -0.0539   0.5398   1.0000
   4.250   0.8000   0.01547   0.00742  -0.0514   0.4373   1.0000
   4.500   0.8150   0.01659   0.00782  -0.0490   0.3233   1.0000
   4.750   0.8336   0.01769   0.00856  -0.0476   0.2714   1.0000
   5.000   0.8543   0.01854   0.00928  -0.0465   0.2354   1.0000
   5.250   0.8750   0.01935   0.01001  -0.0455   0.2048   1.0000
   5.500   0.8952   0.02018   0.01079  -0.0445   0.1659   1.0000
   5.750   0.9135   0.02148   0.01165  -0.0430   0.0857   1.0000
   6.000   0.9283   0.02338   0.01339  -0.0407   0.0662   1.0000
   6.250   0.9476   0.02485   0.01496  -0.0389   0.0586   1.0000
   6.500   0.9657   0.02672   0.01674  -0.0374   0.0536   1.0000
   6.750   0.9880   0.02814   0.01836  -0.0362   0.0493   1.0000
   7.000   1.0098   0.02988   0.02020  -0.0351   0.0462   1.0000
   7.250   1.0324   0.03214   0.02258  -0.0341   0.0447   1.0000
   7.500   1.0550   0.03502   0.02570  -0.0332   0.0439   1.0000
   7.750   1.0755   0.03825   0.02928  -0.0319   0.0437   1.0000
   8.000   1.0920   0.04160   0.03314  -0.0300   0.0442   1.0000
   8.250   1.1033   0.04538   0.03747  -0.0276   0.0446   1.0000
   8.500   1.1102   0.04924   0.04182  -0.0252   0.0446   1.0000
   8.750   1.1125   0.05327   0.04630  -0.0225   0.0446   1.0000
   9.000   1.0896   0.05993   0.05385  -0.0179   0.0473   1.0000
   9.250   1.0733   0.06512   0.05943  -0.0149   0.0486   1.0000
   9.500   1.0543   0.06972   0.06429  -0.0121   0.0496   1.0000
   9.750   1.0328   0.07406   0.06880  -0.0098   0.0505   1.0000
  10.000   1.0118   0.07886   0.07374  -0.0092   0.0513   1.0000
  10.250   0.9929   0.08419   0.07916  -0.0100   0.0520   1.0000
  10.500   0.9778   0.08997   0.08500  -0.0117   0.0528   1.0000
  10.750   0.8479   0.08720   0.08245  -0.0025   0.0531   1.0000
  11.000   0.7893   0.10089   0.09628  -0.0123   0.0553   1.0000
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