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GOE 278 (DAIMLER IX) AIRFOIL (goe278-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 278 (DAIMLER IX) AIRFOIL (goe278-il)
Reynolds number: 1,000,000
Max Cl/Cd: 113.28 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe278-il-1000000.txt
Download as CSV file: xf-goe278-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 278 (DAIMLER IX) AIRFOIL                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2831   0.09289   0.09134  -0.0280   1.0000   0.0123
  -9.250  -0.2795   0.08999   0.08844  -0.0283   1.0000   0.0125
  -9.000  -0.3792   0.09831   0.09667  -0.0235   1.0000   0.0121
  -8.750  -0.3726   0.09530   0.09367  -0.0233   1.0000   0.0122
  -8.500  -0.3669   0.09266   0.09104  -0.0240   1.0000   0.0124
  -8.250  -0.3625   0.09012   0.08852  -0.0247   1.0000   0.0125
  -8.000  -0.3620   0.08782   0.08625  -0.0246   1.0000   0.0127
  -7.750  -0.3727   0.08641   0.08489  -0.0219   1.0000   0.0128
  -7.500  -0.3529   0.08232   0.08080  -0.0280   0.9969   0.0132
  -7.250  -0.3285   0.07776   0.07622  -0.0355   0.9943   0.0140
  -7.000  -0.2907   0.07025   0.06866  -0.0515   0.9881   0.0150
  -6.750  -0.2587   0.06408   0.06242  -0.0611   0.9844   0.0151
  -6.500  -0.2394   0.05858   0.05688  -0.0660   0.9772   0.0153
  -6.250  -0.2165   0.05579   0.05405  -0.0688   0.9717   0.0156
  -6.000  -0.1944   0.05292   0.05114  -0.0716   0.9621   0.0159
  -5.750  -0.1705   0.04985   0.04799  -0.0746   0.9532   0.0165
  -5.500  -0.1340   0.04479   0.04269  -0.0800   0.9435   0.0186
  -5.250  -0.1076   0.04056   0.03828  -0.0822   0.9337   0.0187
  -5.000  -0.0874   0.03524   0.03275  -0.0842   0.9244   0.0190
  -4.750  -0.0662   0.03358   0.03101  -0.0845   0.9147   0.0193
  -4.500  -0.0428   0.03191   0.02924  -0.0849   0.9060   0.0197
  -4.250  -0.0179   0.03007   0.02728  -0.0854   0.8988   0.0206
  -4.000   0.0162   0.02769   0.02457  -0.0852   0.8923   0.0230
  -3.750   0.0425   0.02506   0.02170  -0.0852   0.8854   0.0230
  -3.500   0.0649   0.02115   0.01756  -0.0858   0.8785   0.0238
  -3.250   0.0902   0.02011   0.01642  -0.0859   0.8704   0.0242
  -3.000   0.1163   0.01917   0.01538  -0.0859   0.8622   0.0252
  -2.750   0.1460   0.01885   0.01485  -0.0851   0.8536   0.0283
  -2.500   0.1736   0.01762   0.01339  -0.0848   0.8447   0.0285
  -2.250   0.1989   0.01422   0.00962  -0.0847   0.8357   0.0294
  -2.000   0.2255   0.01345   0.00880  -0.0846   0.8242   0.0301
  -1.750   0.2523   0.01292   0.00819  -0.0845   0.8110   0.0311
  -1.500   0.2795   0.01237   0.00751  -0.0843   0.7953   0.0331
  -1.250   0.3074   0.01295   0.00794  -0.0837   0.7746   0.0355
  -1.000   0.3332   0.01091   0.00559  -0.0834   0.7478   0.0374
  -0.750   0.3589   0.01054   0.00507  -0.0830   0.7073   0.0385
  -0.500   0.3846   0.01034   0.00467  -0.0825   0.6662   0.0400
  -0.250   0.4110   0.01019   0.00436  -0.0821   0.6369   0.0422
   0.000   0.4379   0.00911   0.00306  -0.0813   0.6144   0.0334
   0.250   0.4644   0.00877   0.00261  -0.0810   0.5917   0.0332
   0.500   0.4910   0.00859   0.00233  -0.0807   0.5682   0.0334
   0.750   0.5177   0.00847   0.00211  -0.0804   0.5419   0.0336
   1.000   0.5442   0.00842   0.00194  -0.0801   0.5112   0.0338
   1.250   0.5704   0.00847   0.00184  -0.0798   0.4752   0.0342
   1.500   0.5962   0.00862   0.00180  -0.0795   0.4324   0.0349
   1.750   0.6223   0.00875   0.00176  -0.0792   0.3980   0.0352
   2.000   0.6491   0.00882   0.00175  -0.0790   0.3785   0.0357
   2.250   0.6761   0.00882   0.00167  -0.0788   0.3645   0.0377
   2.500   0.7032   0.00889   0.00169  -0.0787   0.3525   0.0399
   2.750   0.7302   0.00899   0.00174  -0.0786   0.3405   0.0425
   3.000   0.7572   0.00908   0.00181  -0.0784   0.3291   0.0524
   3.250   0.7822   0.00733   0.00209  -0.0784   0.3221   1.0000
   3.500   0.8090   0.00748   0.00218  -0.0782   0.3139   1.0000
   3.750   0.8361   0.00761   0.00227  -0.0781   0.3060   1.0000
   4.000   0.8628   0.00778   0.00239  -0.0779   0.2969   1.0000
   4.250   0.8898   0.00791   0.00250  -0.0778   0.2883   1.0000
   4.500   0.9164   0.00809   0.00262  -0.0776   0.2751   1.0000
   4.750   0.9425   0.00832   0.00277  -0.0774   0.2548   1.0000
   5.000   0.9665   0.00881   0.00300  -0.0768   0.2053   1.0000
   5.250   0.9868   0.00977   0.00354  -0.0758   0.1305   1.0000
   5.500   1.0054   0.01101   0.00430  -0.0745   0.0431   1.0000
   5.750   1.0310   0.01130   0.00460  -0.0742   0.0404   1.0000
   6.000   1.0561   0.01164   0.00494  -0.0738   0.0378   1.0000
   6.250   1.0810   0.01202   0.00533  -0.0733   0.0352   1.0000
   6.500   1.1053   0.01246   0.00583  -0.0727   0.0334   1.0000
   6.750   1.1306   0.01274   0.00615  -0.0724   0.0329   1.0000
   7.000   1.1554   0.01307   0.00650  -0.0720   0.0321   1.0000
   7.250   1.1799   0.01342   0.00689  -0.0715   0.0309   1.0000
   7.500   1.2041   0.01381   0.00731  -0.0710   0.0297   1.0000
   7.750   1.2276   0.01425   0.00778  -0.0705   0.0285   1.0000
   8.000   1.2494   0.01488   0.00845  -0.0696   0.0269   1.0000
   8.250   1.2692   0.01570   0.00937  -0.0684   0.0254   1.0000
   8.500   1.2936   0.01598   0.00968  -0.0680   0.0249   1.0000
   8.750   1.3172   0.01632   0.01005  -0.0675   0.0239   1.0000
   9.000   1.3405   0.01667   0.01042  -0.0670   0.0228   1.0000
   9.250   1.3636   0.01703   0.01079  -0.0664   0.0216   1.0000
   9.500   1.3833   0.01770   0.01149  -0.0653   0.0204   1.0000
   9.750   1.4009   0.01854   0.01241  -0.0639   0.0193   1.0000
  10.000   1.4240   0.01881   0.01272  -0.0634   0.0186   1.0000
  10.250   1.4465   0.01913   0.01306  -0.0628   0.0176   1.0000
  10.500   1.4692   0.01941   0.01335  -0.0622   0.0166   1.0000
  10.750   1.4877   0.02003   0.01397  -0.0611   0.0155   1.0000
  11.000   1.5029   0.02088   0.01490  -0.0594   0.0147   1.0000
  11.250   1.5221   0.02136   0.01544  -0.0583   0.0141   1.0000
  11.500   1.5398   0.02190   0.01602  -0.0570   0.0134   1.0000
  11.750   1.5556   0.02243   0.01659  -0.0554   0.0128   1.0000
  12.000   1.5675   0.02318   0.01737  -0.0533   0.0121   1.0000
  12.250   1.5665   0.02476   0.01906  -0.0495   0.0114   1.0000
  12.500   1.5793   0.02551   0.01988  -0.0477   0.0112   1.0000
  12.750   1.5903   0.02640   0.02086  -0.0459   0.0108   1.0000
  13.000   1.5998   0.02743   0.02197  -0.0441   0.0104   1.0000
  13.250   1.6081   0.02861   0.02322  -0.0423   0.0100   1.0000
  13.500   1.6152   0.02993   0.02463  -0.0406   0.0097   1.0000
  13.750   1.6199   0.03152   0.02628  -0.0390   0.0093   1.0000
  14.000   1.6196   0.03365   0.02851  -0.0372   0.0090   1.0000
  14.250   1.6113   0.03669   0.03168  -0.0355   0.0087   1.0000
  14.500   1.6009   0.04025   0.03539  -0.0343   0.0085   1.0000
  14.750   1.6022   0.04278   0.03804  -0.0339   0.0084   1.0000
  15.000   1.6007   0.04581   0.04119  -0.0338   0.0083   1.0000
  15.250   1.5974   0.04925   0.04476  -0.0341   0.0082   1.0000
  15.500   1.5927   0.05305   0.04870  -0.0347   0.0081   1.0000
  15.750   1.5860   0.05730   0.05307  -0.0357   0.0079   1.0000
  16.000   1.5773   0.06193   0.05784  -0.0369   0.0078   1.0000
  16.250   1.5676   0.06685   0.06289  -0.0384   0.0077   1.0000
  16.500   1.5562   0.07217   0.06833  -0.0401   0.0076   1.0000
  16.750   1.5441   0.07766   0.07395  -0.0420   0.0076   1.0000
  17.000   1.5311   0.08341   0.07981  -0.0440   0.0075   1.0000
  17.250   1.5175   0.08936   0.08588  -0.0463   0.0074   1.0000
  17.500   1.5034   0.09543   0.09207  -0.0486   0.0073   1.0000
  17.750   1.4895   0.10154   0.09829  -0.0510   0.0073   1.0000
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