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GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 279 (DAIMLER X) AIRFOIL (goe279-il)
Reynolds number: 200,000
Max Cl/Cd: 77.41 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe279-il-200000.txt
Download as CSV file: xf-goe279-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 279 (DAIMLER X) AIRFOIL                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3470   0.09971   0.09621  -0.0273   1.0000   0.0280
  -8.000  -0.3568   0.09842   0.09501  -0.0265   1.0000   0.0281
  -7.750  -0.3636   0.09675   0.09342  -0.0271   1.0000   0.0282
  -7.500  -0.3681   0.09486   0.09157  -0.0280   1.0000   0.0282
  -7.250  -0.3703   0.09272   0.08946  -0.0291   1.0000   0.0283
  -7.000  -0.3697   0.09031   0.08705  -0.0304   1.0000   0.0283
  -6.750  -0.3711   0.08632   0.08312  -0.0284   1.0000   0.0285
  -6.500  -0.3726   0.08294   0.07979  -0.0244   1.0000   0.0289
  -6.250  -0.3717   0.08016   0.07704  -0.0225   1.0000   0.0292
  -6.000  -0.3687   0.07746   0.07435  -0.0219   1.0000   0.0296
  -5.750  -0.3632   0.07468   0.07157  -0.0223   1.0000   0.0302
  -5.500  -0.3548   0.07177   0.06864  -0.0233   1.0000   0.0308
  -5.250  -0.3342   0.06813   0.06496  -0.0272   0.9987   0.0321
  -5.000  -0.2623   0.06371   0.06010  -0.0434   0.9944   0.0354
  -4.750  -0.2320   0.05789   0.05416  -0.0484   0.9908   0.0359
  -4.500  -0.2105   0.05351   0.04985  -0.0505   0.9875   0.0368
  -4.250  -0.1775   0.04992   0.04618  -0.0546   0.9846   0.0383
  -4.000  -0.1425   0.04654   0.04266  -0.0586   0.9803   0.0406
  -3.750  -0.0819   0.04509   0.04045  -0.0648   0.9756   0.0448
  -3.500  -0.0552   0.03896   0.03452  -0.0687   0.9731   0.0469
  -3.250  -0.0180   0.03629   0.03173  -0.0721   0.9687   0.0508
  -3.000   0.0301   0.03358   0.02844  -0.0758   0.9629   0.0570
  -2.750   0.0715   0.03038   0.02526  -0.0803   0.9593   0.0610
  -2.500   0.1142   0.02811   0.02263  -0.0834   0.9540   0.0715
  -2.250   0.1554   0.02625   0.02048  -0.0863   0.9480   0.0850
  -2.000   0.2018   0.02399   0.01811  -0.0907   0.9446   0.1011
  -1.000  -0.3126   0.05859   0.05572   0.0014   0.8952   0.0520
  -0.750   0.4026   0.01687   0.00963  -0.0983   0.9161   0.0821
  -0.500   0.4347   0.01534   0.00807  -0.0985   0.9077   0.0765
  -0.250   0.4681   0.01447   0.00712  -0.0988   0.8997   0.0764
   0.000   0.4962   0.01379   0.00643  -0.0981   0.8879   0.0762
   0.250   0.5246   0.01315   0.00579  -0.0975   0.8757   0.0758
   0.500   0.5524   0.01261   0.00526  -0.0968   0.8622   0.0768
   0.750   0.5797   0.01218   0.00484  -0.0961   0.8469   0.0796
   1.000   0.6067   0.01185   0.00449  -0.0954   0.8297   0.0833
   1.250   0.6338   0.01149   0.00409  -0.0946   0.8099   0.0880
   1.500   0.6600   0.01131   0.00384  -0.0937   0.7843   0.0957
   1.750   0.6824   0.00985   0.00378  -0.0927   0.7561   0.6812
   2.000   0.7057   0.00929   0.00352  -0.0905   0.7214   1.0000
   2.250   0.7309   0.00945   0.00338  -0.0894   0.6801   1.0000
   2.500   0.7555   0.00976   0.00336  -0.0884   0.6410   1.0000
   2.750   0.7800   0.01013   0.00347  -0.0875   0.6058   1.0000
   3.000   0.8045   0.01052   0.00364  -0.0868   0.5730   1.0000
   3.250   0.8287   0.01091   0.00382  -0.0860   0.5391   1.0000
   3.500   0.8529   0.01128   0.00401  -0.0852   0.5047   1.0000
   3.750   0.8771   0.01166   0.00424  -0.0845   0.4735   1.0000
   4.000   0.9013   0.01205   0.00447  -0.0839   0.4467   1.0000
   4.250   0.9261   0.01242   0.00473  -0.0833   0.4243   1.0000
   4.500   0.9505   0.01283   0.00501  -0.0827   0.4046   1.0000
   4.750   0.9751   0.01322   0.00532  -0.0822   0.3865   1.0000
   5.000   0.9997   0.01361   0.00564  -0.0817   0.3700   1.0000
   5.250   1.0243   0.01401   0.00599  -0.0812   0.3556   1.0000
   5.500   1.0488   0.01442   0.00635  -0.0807   0.3417   1.0000
   5.750   1.0731   0.01482   0.00673  -0.0802   0.3276   1.0000
   6.000   1.0971   0.01521   0.00710  -0.0796   0.3129   1.0000
   6.250   1.1214   0.01557   0.00749  -0.0791   0.2991   1.0000
   6.500   1.1455   0.01592   0.00789  -0.0785   0.2852   1.0000
   6.750   1.1693   0.01628   0.00830  -0.0779   0.2703   1.0000
   7.000   1.1926   0.01666   0.00870  -0.0773   0.2545   1.0000
   7.250   1.2159   0.01702   0.00909  -0.0766   0.2356   1.0000
   7.500   1.2387   0.01742   0.00953  -0.0759   0.2162   1.0000
   7.750   1.2606   0.01792   0.01001  -0.0751   0.1975   1.0000
   8.000   1.2823   0.01845   0.01053  -0.0742   0.1768   1.0000
   8.500   1.3204   0.02004   0.01197  -0.0719   0.1294   1.0000
   8.750   1.3361   0.02120   0.01300  -0.0703   0.1012   1.0000
   9.000   1.3530   0.02223   0.01395  -0.0687   0.0776   1.0000
   9.250   1.3681   0.02334   0.01499  -0.0669   0.0671   1.0000
   9.500   1.3823   0.02444   0.01615  -0.0650   0.0616   1.0000
   9.750   1.3935   0.02572   0.01748  -0.0627   0.0574   1.0000
  10.000   1.4019   0.02714   0.01897  -0.0600   0.0543   1.0000
  10.250   1.4103   0.02836   0.02033  -0.0573   0.0517   1.0000
  10.500   1.4164   0.02980   0.02186  -0.0544   0.0491   1.0000
  10.750   1.4182   0.03171   0.02379  -0.0513   0.0467   1.0000
  11.000   1.4225   0.03373   0.02591  -0.0485   0.0447   1.0000
  11.250   1.4302   0.03536   0.02773  -0.0463   0.0429   1.0000
  11.500   1.4365   0.03717   0.02967  -0.0441   0.0408   1.0000
  11.750   1.4418   0.03918   0.03174  -0.0421   0.0387   1.0000
  12.000   1.4535   0.04299   0.03555  -0.0406   0.0361   1.0000
  12.250   1.4558   0.04480   0.03761  -0.0383   0.0353   1.0000
  12.500   1.4577   0.04700   0.04007  -0.0363   0.0342   1.0000
  12.750   1.4582   0.04945   0.04274  -0.0345   0.0329   1.0000
  13.000   1.4589   0.05199   0.04545  -0.0330   0.0316   1.0000
  13.250   1.4576   0.05473   0.04835  -0.0316   0.0304   1.0000
  13.500   1.4573   0.05778   0.05150  -0.0305   0.0294   1.0000
  13.750   1.4559   0.06186   0.05573  -0.0293   0.0285   1.0000
  14.000   1.4444   0.06729   0.06143  -0.0283   0.0280   1.0000
  14.250   1.4270   0.07245   0.06686  -0.0279   0.0278   1.0000
  14.500   1.4104   0.07694   0.07160  -0.0284   0.0277   1.0000
  14.750   1.3930   0.08204   0.07694  -0.0296   0.0276   1.0000
  15.000   1.3744   0.08772   0.08285  -0.0316   0.0276   1.0000
  15.250   1.3549   0.09398   0.08934  -0.0343   0.0276   1.0000
  15.500   1.3347   0.10080   0.09636  -0.0377   0.0276   1.0000
  15.750   1.3138   0.10826   0.10402  -0.0417   0.0277   1.0000
  16.000   1.2923   0.11639   0.11234  -0.0463   0.0278   1.0000
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