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GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 276 (DAIMLER VII) AIRFOIL (goe276-il)
Reynolds number: 1,000,000
Max Cl/Cd: 114.08 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe276-il-1000000.txt
Download as CSV file: xf-goe276-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 276 (DAIMLER VII) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3857   0.09186   0.09028  -0.0180   1.0000   0.0129
  -7.750  -0.3932   0.08914   0.08760  -0.0179   1.0000   0.0136
  -7.500  -0.3929   0.08560   0.08409  -0.0206   1.0000   0.0137
  -7.250  -0.3894   0.08178   0.08029  -0.0238   1.0000   0.0137
  -7.000  -0.3771   0.07731   0.07581  -0.0285   0.9994   0.0138
  -6.750  -0.3482   0.07130   0.06976  -0.0374   0.9973   0.0138
  -6.500  -0.3281   0.06623   0.06468  -0.0421   0.9954   0.0142
  -6.250  -0.2999   0.06280   0.06121  -0.0474   0.9933   0.0146
  -6.000  -0.2697   0.05913   0.05750  -0.0531   0.9895   0.0153
  -5.750  -0.2183   0.05190   0.05009  -0.0654   0.9859   0.0175
  -5.250  -0.1506   0.03863   0.03646  -0.0781   0.9737   0.0181
  -5.000  -0.1218   0.03703   0.03483  -0.0804   0.9632   0.0185
  -4.750  -0.0883   0.03514   0.03284  -0.0835   0.9509   0.0196
  -4.500  -0.0440   0.03183   0.02921  -0.0865   0.9357   0.0223
  -4.250  -0.0128   0.02845   0.02552  -0.0880   0.9183   0.0224
  -4.000   0.0135   0.02297   0.01963  -0.0900   0.9042   0.0234
  -3.750   0.0394   0.02212   0.01869  -0.0904   0.8924   0.0240
  -3.500   0.0664   0.02104   0.01747  -0.0907   0.8817   0.0250
  -3.250   0.0949   0.01992   0.01616  -0.0907   0.8712   0.0272
  -3.000   0.1250   0.01993   0.01595  -0.0901   0.8611   0.0288
  -2.750   0.1540   0.01851   0.01429  -0.0903   0.8519   0.0289
  -2.500   0.1830   0.01455   0.00990  -0.0913   0.8421   0.0304
  -2.250   0.2106   0.01385   0.00911  -0.0914   0.8286   0.0311
  -2.000   0.2384   0.01324   0.00839  -0.0914   0.8120   0.0321
  -1.750   0.2665   0.01268   0.00769  -0.0914   0.7929   0.0334
  -1.500   0.2944   0.01238   0.00722  -0.0912   0.7693   0.0357
  -0.750   0.3716   0.01249   0.00687  -0.0956   0.5789   0.0342
  -0.500   0.4004   0.01072   0.00407  -0.0897   0.4801   0.0348
  -0.250   0.4281   0.01033   0.00350  -0.0896   0.4530   0.0337
   0.000   0.4562   0.01001   0.00310  -0.0896   0.4388   0.0332
   0.250   0.4844   0.00983   0.00287  -0.0897   0.4287   0.0336
   0.500   0.5128   0.00960   0.00259  -0.0897   0.4201   0.0336
   0.750   0.5411   0.00946   0.00241  -0.0898   0.4129   0.0341
   1.000   0.5696   0.00936   0.00229  -0.0899   0.4066   0.0353
   1.250   0.5978   0.00933   0.00222  -0.0900   0.4002   0.0362
   1.500   0.6262   0.00928   0.00216  -0.0901   0.3939   0.0370
   1.750   0.6543   0.00929   0.00214  -0.0901   0.3874   0.0375
   2.000   0.6827   0.00925   0.00209  -0.0902   0.3820   0.0386
   2.250   0.7110   0.00923   0.00205  -0.0902   0.3759   0.0425
   2.500   0.7391   0.00926   0.00207  -0.0903   0.3694   0.0485
   2.750   0.7619   0.00738   0.00226  -0.0898   0.3630   1.0000
   3.000   0.7898   0.00751   0.00232  -0.0898   0.3551   1.0000
   3.250   0.8178   0.00760   0.00239  -0.0898   0.3474   1.0000
   3.500   0.8457   0.00772   0.00247  -0.0898   0.3387   1.0000
   3.750   0.8734   0.00785   0.00257  -0.0898   0.3288   1.0000
   4.000   0.9012   0.00798   0.00267  -0.0898   0.3183   1.0000
   4.250   0.9286   0.00814   0.00278  -0.0898   0.3052   1.0000
   4.500   0.9554   0.00839   0.00291  -0.0897   0.2831   1.0000
   4.750   0.9823   0.00863   0.00308  -0.0896   0.2641   1.0000
   5.000   1.0087   0.00891   0.00327  -0.0894   0.2447   1.0000
   5.250   1.0350   0.00922   0.00348  -0.0892   0.2244   1.0000
   5.500   1.0612   0.00953   0.00370  -0.0891   0.2052   1.0000
   5.750   1.0871   0.00988   0.00396  -0.0888   0.1830   1.0000
   6.000   1.1120   0.01037   0.00427  -0.0885   0.1490   1.0000
   6.250   1.1369   0.01086   0.00462  -0.0881   0.1256   1.0000
   6.500   1.1624   0.01125   0.00496  -0.0878   0.1121   1.0000
   6.750   1.1870   0.01176   0.00534  -0.0874   0.0901   1.0000
   7.000   1.2051   0.01325   0.00638  -0.0861   0.0197   1.0000
   7.250   1.2293   0.01381   0.00695  -0.0855   0.0153   1.0000
   7.500   1.2543   0.01421   0.00739  -0.0851   0.0143   1.0000
   7.750   1.2785   0.01469   0.00794  -0.0845   0.0132   1.0000
   8.000   1.3018   0.01530   0.00860  -0.0838   0.0121   1.0000
   8.250   1.3230   0.01618   0.00960  -0.0828   0.0111   1.0000
   8.500   1.3465   0.01667   0.01014  -0.0822   0.0108   1.0000
   8.750   1.3694   0.01722   0.01076  -0.0814   0.0102   1.0000
   9.000   1.3917   0.01779   0.01139  -0.0807   0.0096   1.0000
   9.250   1.4130   0.01845   0.01209  -0.0797   0.0091   1.0000
   9.500   1.4327   0.01926   0.01297  -0.0786   0.0086   1.0000
   9.750   1.4451   0.02079   0.01463  -0.0763   0.0081   1.0000
  10.000   1.4593   0.02200   0.01597  -0.0743   0.0079   1.0000
  10.250   1.4777   0.02274   0.01678  -0.0729   0.0077   1.0000
  10.500   1.4937   0.02363   0.01776  -0.0712   0.0075   1.0000
  10.750   1.5079   0.02462   0.01884  -0.0693   0.0072   1.0000
  11.000   1.5196   0.02569   0.02001  -0.0670   0.0070   1.0000
  11.250   1.5292   0.02680   0.02120  -0.0644   0.0069   1.0000
  11.500   1.5356   0.02792   0.02242  -0.0613   0.0067   1.0000
  11.750   1.5401   0.02906   0.02365  -0.0580   0.0065   1.0000
  12.000   1.5454   0.03026   0.02493  -0.0552   0.0063   1.0000
  12.250   1.5501   0.03160   0.02634  -0.0526   0.0061   1.0000
  12.500   1.5521   0.03325   0.02807  -0.0501   0.0060   1.0000
  12.750   1.5498   0.03543   0.03036  -0.0477   0.0058   1.0000
  13.000   1.5404   0.03854   0.03360  -0.0453   0.0057   1.0000
  13.250   1.5251   0.04258   0.03780  -0.0431   0.0056   1.0000
  13.500   1.5100   0.04697   0.04235  -0.0415   0.0055   1.0000
  13.750   1.5086   0.05000   0.04552  -0.0414   0.0054   1.0000
  14.000   1.5058   0.05344   0.04909  -0.0416   0.0054   1.0000
  14.250   1.5013   0.05732   0.05312  -0.0424   0.0053   1.0000
  14.500   1.4937   0.06188   0.05782  -0.0435   0.0053   1.0000
  14.750   1.4856   0.06679   0.06287  -0.0451   0.0053   1.0000
  15.000   1.4759   0.07207   0.06829  -0.0471   0.0052   1.0000
  15.250   1.4651   0.07773   0.07409  -0.0493   0.0052   1.0000
  15.500   1.4533   0.08368   0.08018  -0.0518   0.0052   1.0000
  15.750   1.4406   0.08982   0.08646  -0.0544   0.0051   1.0000
  16.000   1.4270   0.09616   0.09293  -0.0571   0.0051   1.0000
  16.250   1.4124   0.10278   0.09968  -0.0600   0.0051   1.0000
  16.500   1.3979   0.10948   0.10650  -0.0630   0.0051   1.0000
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