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GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 275 (DAIMLER VI) AIRFOIL (goe275-il)
Reynolds number: 500,000
Max Cl/Cd: 94.35 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe275-il-500000-n5.txt
Download as CSV file: xf-goe275-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 275 (DAIMLER VI) AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3269   0.10320   0.10090  -0.0235   1.0000   0.0100
  -9.000  -0.3244   0.10081   0.09853  -0.0234   1.0000   0.0097
  -8.750  -0.3222   0.09863   0.09638  -0.0232   1.0000   0.0106
  -8.500  -0.3205   0.09666   0.09445  -0.0227   1.0000   0.0111
  -8.250  -0.3125   0.09222   0.09002  -0.0261   0.9985   0.0105
  -8.000  -0.2964   0.08804   0.08584  -0.0309   0.9953   0.0106
  -7.750  -0.2804   0.08465   0.08246  -0.0350   0.9909   0.0109
  -7.500  -0.2641   0.08064   0.07845  -0.0401   0.9858   0.0110
  -7.000  -0.2297   0.07238   0.07018  -0.0507   0.9672   0.0114
  -6.750  -0.2102   0.06800   0.06579  -0.0566   0.9564   0.0120
  -6.500  -0.1833   0.06236   0.06009  -0.0654   0.9476   0.0129
  -6.250  -0.1535   0.05839   0.05607  -0.0720   0.9409   0.0132
  -6.000  -0.1176   0.05412   0.05173  -0.0798   0.9350   0.0137
  -5.750  -0.0800   0.04933   0.04683  -0.0879   0.9274   0.0143
  -5.500  -0.0388   0.04334   0.04064  -0.0969   0.9183   0.0158
  -5.000   0.0265   0.03734   0.03433  -0.1047   0.8943   0.0170
  -4.750   0.0571   0.03218   0.02880  -0.1076   0.8813   0.0185
  -4.500   0.0808   0.03081   0.02732  -0.1082   0.8678   0.0193
  -4.250   0.1051   0.02919   0.02557  -0.1086   0.8555   0.0200
  -4.000   0.1302   0.02672   0.02286  -0.1089   0.8438   0.0204
  -3.750   0.1584   0.02291   0.01845  -0.1082   0.8318   0.0225
  -3.500   0.1806   0.02211   0.01767  -0.1082   0.8168   0.0231
  -3.250   0.2042   0.02136   0.01681  -0.1079   0.7990   0.0241
  -3.000   0.2284   0.01967   0.01481  -0.1071   0.7752   0.0241
  -2.750   0.2515   0.01837   0.01316  -0.1060   0.7391   0.0243
  -2.500   0.2731   0.01741   0.01178  -0.1045   0.6906   0.0246
  -2.250   0.2949   0.01670   0.01066  -0.1030   0.6438   0.0256
  -2.000   0.3180   0.01585   0.00946  -0.1018   0.6100   0.0256
  -1.750   0.3422   0.01510   0.00842  -0.1008   0.5825   0.0257
  -1.500   0.3668   0.01448   0.00753  -0.1000   0.5570   0.0260
  -1.250   0.3916   0.01396   0.00677  -0.0991   0.5326   0.0261
  -1.000   0.4169   0.01388   0.00643  -0.0983   0.5070   0.0268
  -0.750   0.4416   0.01341   0.00573  -0.0976   0.4808   0.0272
  -0.500   0.4663   0.01310   0.00524  -0.0968   0.4535   0.0271
  -0.250   0.4910   0.01270   0.00468  -0.0961   0.4281   0.0272
   0.000   0.5157   0.01233   0.00419  -0.0954   0.4062   0.0274
   0.250   0.5405   0.01206   0.00383  -0.0948   0.3872   0.0278
   0.500   0.5656   0.01190   0.00358  -0.0942   0.3712   0.0281
   0.750   0.5907   0.01177   0.00340  -0.0936   0.3591   0.0285
   1.000   0.6164   0.01164   0.00325  -0.0931   0.3507   0.0290
   1.250   0.6418   0.01158   0.00315  -0.0925   0.3424   0.0298
   1.500   0.6675   0.01152   0.00306  -0.0920   0.3335   0.0304
   1.750   0.6929   0.01147   0.00297  -0.0915   0.3257   0.0306
   2.000   0.7187   0.01142   0.00291  -0.0910   0.3185   0.0307
   2.250   0.7441   0.01143   0.00288  -0.0905   0.3115   0.0312
   2.500   0.7702   0.01142   0.00286  -0.0900   0.3062   0.0317
   2.750   0.7960   0.01144   0.00288  -0.0896   0.3003   0.0323
   3.250   0.8478   0.01152   0.00293  -0.0887   0.2899   0.0338
   3.500   0.8736   0.01157   0.00298  -0.0883   0.2845   0.0363
   3.750   0.8992   0.01168   0.00306  -0.0878   0.2786   0.0376
   4.000   0.9251   0.01176   0.00315  -0.0874   0.2725   0.0390
   4.500   0.9811   0.01047   0.00363  -0.0881   0.2532   1.0000
   4.750   1.0060   0.01067   0.00377  -0.0875   0.2409   1.0000
   5.000   1.0303   0.01092   0.00393  -0.0868   0.2237   1.0000
   5.250   1.0536   0.01127   0.00414  -0.0860   0.1992   1.0000
   5.500   1.0766   0.01164   0.00441  -0.0852   0.1827   1.0000
   5.750   1.1000   0.01197   0.00468  -0.0845   0.1725   1.0000
   6.000   1.1235   0.01229   0.00496  -0.0837   0.1650   1.0000
   6.250   1.1474   0.01257   0.00523  -0.0830   0.1586   1.0000
   6.500   1.1706   0.01290   0.00555  -0.0822   0.1523   1.0000
   6.750   1.1946   0.01315   0.00582  -0.0816   0.1475   1.0000
   7.000   1.2180   0.01344   0.00612  -0.0808   0.1402   1.0000
   7.250   1.2411   0.01376   0.00644  -0.0801   0.1323   1.0000
   7.750   1.2820   0.01487   0.00730  -0.0778   0.0907   1.0000
   8.000   1.3034   0.01531   0.00774  -0.0768   0.0852   1.0000
   8.250   1.3241   0.01579   0.00823  -0.0757   0.0808   1.0000
   8.500   1.3439   0.01632   0.00877  -0.0745   0.0759   1.0000
   8.750   1.3651   0.01671   0.00921  -0.0735   0.0737   1.0000
   9.000   1.3864   0.01706   0.00962  -0.0725   0.0713   1.0000
   9.250   1.4067   0.01748   0.01010  -0.0713   0.0685   1.0000
   9.500   1.4257   0.01797   0.01062  -0.0700   0.0656   1.0000
   9.750   1.4437   0.01852   0.01121  -0.0686   0.0628   1.0000
  10.000   1.4631   0.01890   0.01166  -0.0673   0.0608   1.0000
  10.250   1.4813   0.01929   0.01212  -0.0658   0.0581   1.0000
  10.500   1.4972   0.01980   0.01264  -0.0640   0.0535   1.0000
  10.750   1.5122   0.02034   0.01320  -0.0621   0.0488   1.0000
  11.000   1.5245   0.02105   0.01385  -0.0599   0.0388   1.0000
  11.500   1.5304   0.02364   0.01631  -0.0531   0.0150   1.0000
  11.750   1.5382   0.02463   0.01739  -0.0506   0.0130   1.0000
  12.000   1.5463   0.02564   0.01849  -0.0482   0.0119   1.0000
  12.250   1.5524   0.02681   0.01975  -0.0458   0.0110   1.0000
  12.500   1.5564   0.02818   0.02122  -0.0433   0.0102   1.0000
  12.750   1.5629   0.02942   0.02257  -0.0413   0.0098   1.0000
  13.000   1.5679   0.03083   0.02410  -0.0394   0.0093   1.0000
  13.250   1.5712   0.03244   0.02582  -0.0376   0.0089   1.0000
  13.500   1.5736   0.03422   0.02771  -0.0359   0.0086   1.0000
  13.750   1.5737   0.03630   0.02990  -0.0345   0.0082   1.0000
  14.000   1.5711   0.03879   0.03251  -0.0332   0.0078   1.0000
  14.250   1.5654   0.04181   0.03567  -0.0323   0.0076   1.0000
  14.500   1.5617   0.04484   0.03882  -0.0320   0.0073   1.0000
  14.750   1.5583   0.04805   0.04217  -0.0320   0.0072   1.0000
  15.000   1.5514   0.05194   0.04621  -0.0325   0.0070   1.0000
  15.250   1.5440   0.05615   0.05055  -0.0335   0.0069   1.0000
  15.500   1.5344   0.06089   0.05544  -0.0348   0.0067   1.0000
  15.750   1.5232   0.06609   0.06079  -0.0366   0.0066   1.0000
  16.000   1.5101   0.07181   0.06666  -0.0387   0.0066   1.0000
  16.250   1.4957   0.07793   0.07293  -0.0412   0.0065   1.0000
  16.500   1.4808   0.08429   0.07944  -0.0439   0.0064   1.0000
  16.750   1.4647   0.09102   0.08631  -0.0469   0.0064   1.0000
  17.000   1.4494   0.09770   0.09312  -0.0499   0.0064   1.0000
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