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GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.14 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe277-il-1000000-n5.txt
Download as CSV file: xf-goe277-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 277 (DAIMLER VIII) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4051   0.11398   0.11233  -0.0136   1.0000   0.0051
 -10.250  -0.4077   0.10821   0.10657  -0.0158   1.0000   0.0054
 -10.000  -0.4059   0.10396   0.10233  -0.0177   1.0000   0.0056
  -9.750  -0.3995   0.10098   0.09937  -0.0191   1.0000   0.0057
  -9.500  -0.3930   0.09804   0.09644  -0.0206   1.0000   0.0058
  -9.250  -0.3869   0.09505   0.09347  -0.0221   1.0000   0.0060
  -8.750  -0.3789   0.08843   0.08688  -0.0254   1.0000   0.0065
  -7.250  -0.3067   0.04706   0.04515  -0.0738   0.9261   0.0103
  -7.000  -0.2840   0.04433   0.04232  -0.0762   0.9141   0.0107
  -6.750  -0.2661   0.02575   0.02287  -0.0869   0.9041   0.0138
  -6.250  -0.2245   0.01453   0.01036  -0.0881   0.8786   0.0179
  -6.000  -0.1983   0.01390   0.00954  -0.0879   0.8605   0.0184
  -5.750  -0.1715   0.01392   0.00947  -0.0876   0.8356   0.0188
  -5.500  -0.1453   0.01408   0.00946  -0.0872   0.7934   0.0191
  -5.250  -0.1189   0.01438   0.00958  -0.0868   0.7511   0.0194
  -5.000  -0.0919   0.01446   0.00954  -0.0866   0.7262   0.0198
  -4.750  -0.0644   0.01421   0.00916  -0.0866   0.7116   0.0203
  -4.500  -0.0369   0.01389   0.00871  -0.0866   0.6990   0.0210
  -4.250  -0.0093   0.01330   0.00795  -0.0866   0.6863   0.0217
  -4.000   0.0184   0.01274   0.00723  -0.0866   0.6724   0.0223
  -3.750   0.0461   0.01239   0.00674  -0.0866   0.6568   0.0229
  -3.500   0.0739   0.01198   0.00618  -0.0866   0.6406   0.0233
  -3.250   0.1017   0.01158   0.00564  -0.0866   0.6229   0.0235
  -3.000   0.1294   0.01121   0.00513  -0.0865   0.6022   0.0237
  -2.750   0.1570   0.01092   0.00469  -0.0865   0.5801   0.0239
  -2.500   0.1847   0.01067   0.00429  -0.0864   0.5577   0.0240
  -2.250   0.2123   0.01052   0.00402  -0.0864   0.5367   0.0242
  -2.000   0.2398   0.00994   0.00329  -0.0864   0.5187   0.0248
  -1.750   0.2674   0.00950   0.00274  -0.0864   0.5037   0.0254
  -1.500   0.2953   0.00929   0.00245  -0.0864   0.4897   0.0261
  -1.250   0.3233   0.00917   0.00227  -0.0864   0.4756   0.0267
  -1.000   0.3513   0.00910   0.00214  -0.0864   0.4611   0.0273
  -0.750   0.3793   0.00905   0.00201  -0.0864   0.4460   0.0278
  -0.500   0.4072   0.00901   0.00190  -0.0865   0.4296   0.0282
  -0.250   0.4351   0.00900   0.00181  -0.0865   0.4112   0.0287
   0.000   0.4629   0.00901   0.00173  -0.0865   0.3930   0.0290
   0.250   0.4907   0.00903   0.00167  -0.0865   0.3776   0.0294
   0.500   0.5187   0.00904   0.00162  -0.0865   0.3659   0.0297
   0.750   0.5466   0.00907   0.00160  -0.0865   0.3559   0.0303
   1.000   0.5746   0.00909   0.00159  -0.0865   0.3473   0.0310
   1.250   0.6026   0.00912   0.00158  -0.0865   0.3405   0.0315
   1.500   0.6306   0.00915   0.00158  -0.0865   0.3342   0.0321
   1.750   0.6584   0.00920   0.00161  -0.0866   0.3282   0.0330
   2.000   0.6864   0.00924   0.00163  -0.0866   0.3225   0.0362
   3.000   0.7924   0.00767   0.00212  -0.0862   0.2991   1.0000
   3.250   0.8203   0.00777   0.00221  -0.0862   0.2961   1.0000
   3.500   0.8481   0.00787   0.00230  -0.0862   0.2924   1.0000
   3.750   0.8757   0.00800   0.00240  -0.0862   0.2884   1.0000
   4.000   0.9032   0.00813   0.00252  -0.0862   0.2848   1.0000
   4.250   0.9309   0.00824   0.00263  -0.0862   0.2816   1.0000
   4.500   0.9584   0.00836   0.00274  -0.0862   0.2766   1.0000
   4.750   0.9858   0.00851   0.00288  -0.0861   0.2723   1.0000
   5.000   1.0130   0.00865   0.00301  -0.0861   0.2660   1.0000
   5.250   1.0399   0.00884   0.00316  -0.0860   0.2563   1.0000
   5.500   1.0668   0.00903   0.00331  -0.0860   0.2448   1.0000
   5.750   1.0928   0.00931   0.00351  -0.0858   0.2263   1.0000
   6.000   1.1158   0.00997   0.00388  -0.0852   0.1756   1.0000
   6.250   1.1362   0.01097   0.00453  -0.0843   0.1142   1.0000
   6.500   1.1595   0.01158   0.00499  -0.0838   0.0874   1.0000
   6.750   1.1844   0.01197   0.00534  -0.0834   0.0759   1.0000
   7.000   1.2087   0.01240   0.00571  -0.0830   0.0620   1.0000
   7.250   1.2275   0.01353   0.00655  -0.0818   0.0166   1.0000
   7.500   1.2519   0.01391   0.00696  -0.0814   0.0130   1.0000
   7.750   1.2758   0.01434   0.00740  -0.0809   0.0109   1.0000
   8.000   1.2998   0.01473   0.00782  -0.0804   0.0099   1.0000
   8.250   1.3236   0.01511   0.00824  -0.0799   0.0091   1.0000
   8.500   1.3468   0.01556   0.00871  -0.0794   0.0082   1.0000
   8.750   1.3689   0.01610   0.00929  -0.0786   0.0072   1.0000
   9.000   1.3915   0.01654   0.00977  -0.0780   0.0068   1.0000
   9.250   1.4137   0.01701   0.01029  -0.0773   0.0064   1.0000
   9.500   1.4352   0.01751   0.01083  -0.0765   0.0060   1.0000
   9.750   1.4560   0.01806   0.01141  -0.0756   0.0056   1.0000
  10.000   1.4756   0.01867   0.01208  -0.0745   0.0053   1.0000
  10.250   1.4930   0.01946   0.01293  -0.0731   0.0049   1.0000
  10.500   1.5119   0.02005   0.01358  -0.0720   0.0047   1.0000
  10.750   1.5297   0.02068   0.01428  -0.0707   0.0045   1.0000
  11.000   1.5464   0.02135   0.01500  -0.0693   0.0043   1.0000
  11.250   1.5614   0.02205   0.01577  -0.0676   0.0041   1.0000
  11.500   1.5728   0.02279   0.01657  -0.0653   0.0039   1.0000
  11.750   1.5829   0.02363   0.01749  -0.0630   0.0038   1.0000
  12.000   1.5921   0.02457   0.01849  -0.0607   0.0037   1.0000
  12.250   1.5995   0.02568   0.01967  -0.0584   0.0035   1.0000
  12.500   1.6044   0.02703   0.02111  -0.0560   0.0034   1.0000
  12.750   1.6051   0.02881   0.02300  -0.0536   0.0033   1.0000
  13.000   1.6090   0.03047   0.02475  -0.0518   0.0032   1.0000
  13.250   1.6129   0.03226   0.02664  -0.0503   0.0032   1.0000
  13.500   1.6150   0.03434   0.02883  -0.0490   0.0031   1.0000
  13.750   1.6158   0.03674   0.03134  -0.0481   0.0031   1.0000
  14.000   1.6154   0.03946   0.03418  -0.0476   0.0030   1.0000
  14.250   1.6134   0.04255   0.03738  -0.0475   0.0030   1.0000
  14.500   1.6092   0.04610   0.04106  -0.0476   0.0029   1.0000
  14.750   1.6040   0.04989   0.04498  -0.0481   0.0029   1.0000
  15.000   1.5960   0.05423   0.04944  -0.0488   0.0028   1.0000
  15.250   1.5876   0.05876   0.05410  -0.0498   0.0028   1.0000
  15.500   1.5769   0.06373   0.05920  -0.0510   0.0028   1.0000
  15.750   1.5652   0.06897   0.06456  -0.0525   0.0027   1.0000
  16.000   1.5515   0.07461   0.07032  -0.0541   0.0027   1.0000
  16.250   1.5372   0.08038   0.07621  -0.0558   0.0027   1.0000
  16.500   1.5226   0.08632   0.08227  -0.0576   0.0027   1.0000
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