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GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 275 (DAIMLER VI) AIRFOIL (goe275-il)
Reynolds number: 50,000
Max Cl/Cd: 34.44 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe275-il-50000.txt
Download as CSV file: xf-goe275-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3349   0.11089   0.10387  -0.0224   1.0000   0.1288
  -8.500  -0.3448   0.11051   0.10362  -0.0234   1.0000   0.1322
  -8.250  -0.3606   0.11077   0.10405  -0.0239   1.0000   0.1331
  -8.000  -0.3315   0.10325   0.09646  -0.0216   1.0000   0.1411
  -7.750  -0.3383   0.10195   0.09529  -0.0212   1.0000   0.1461
  -7.500  -0.3553   0.10203   0.09555  -0.0222   1.0000   0.1483
  -7.250  -0.3393   0.09674   0.09027  -0.0190   1.0000   0.1561
  -7.000  -0.3480   0.09564   0.08932  -0.0198   1.0000   0.1625
  -6.750  -0.3475   0.09259   0.08636  -0.0191   1.0000   0.1674
  -6.500  -0.3457   0.09024   0.08409  -0.0181   1.0000   0.1767
  -6.250  -0.3485   0.08783   0.08178  -0.0186   1.0000   0.1825
  -6.000  -0.3467   0.08557   0.07958  -0.0178   1.0000   0.1933
  -5.500  -0.3453   0.08091   0.07505  -0.0194   1.0000   0.2122
  -5.250  -0.3414   0.07872   0.07288  -0.0195   1.0000   0.2268
  -5.000  -0.3368   0.07505   0.06931  -0.0144   1.0000   0.2388
  -4.750  -0.3321   0.07340   0.06765  -0.0179   1.0000   0.2589
  -4.500  -0.3289   0.07005   0.06441  -0.0140   1.0000   0.2762
  -4.250  -0.3257   0.06731   0.06176  -0.0098   1.0000   0.2981
  -4.000   0.0713   0.04106   0.03457  -0.0277   1.0000   1.0000
  -3.750   0.0779   0.03962   0.03322  -0.0273   1.0000   1.0000
  -3.500   0.0840   0.03828   0.03198  -0.0268   1.0000   1.0000
  -3.250   0.0892   0.03703   0.03083  -0.0262   1.0000   1.0000
  -3.000   0.0934   0.03586   0.02978  -0.0254   1.0000   1.0000
  -2.750   0.0524   0.03684   0.03100  -0.0140   1.0000   0.9840
  -2.500   0.0040   0.03780   0.03221  -0.0017   1.0000   0.9616
  -2.250  -0.0472   0.03869   0.03333   0.0104   1.0000   0.9417
  -2.000  -0.0955   0.03907   0.03394   0.0210   1.0000   0.9205
  -1.750  -0.1454   0.03922   0.03433   0.0313   1.0000   0.9012
  -1.500  -0.1993   0.03928   0.03461   0.0420   1.0000   0.8851
  -1.250  -0.2646   0.03927   0.03484   0.0545   1.0000   0.8702
  -1.000  -0.0190   0.03619   0.02889  -0.0419   1.0000   0.3087
  -0.750   0.0213   0.03541   0.02728  -0.0452   1.0000   0.2417
  -0.500   0.0541   0.03434   0.02589  -0.0471   0.9970   0.2174
  -0.250   0.1248   0.03338   0.02424  -0.0546   0.9789   0.1864
   0.000   0.1916   0.03257   0.02285  -0.0611   0.9600   0.1686
   0.250   0.2492   0.03186   0.02179  -0.0661   0.9379   0.1602
   0.500   0.3136   0.03103   0.02068  -0.0719   0.9174   0.1600
   0.750   0.3696   0.03026   0.01973  -0.0760   0.8933   0.1606
   1.000   0.4320   0.02926   0.01864  -0.0808   0.8715   0.1624
   1.250   0.4842   0.02834   0.01773  -0.0840   0.8464   0.1691
   1.500   0.5466   0.02707   0.01660  -0.0885   0.8251   0.1971
   1.750   0.5980   0.02453   0.01588  -0.0910   0.8011   1.0000
   2.000   0.6482   0.02400   0.01490  -0.0925   0.7782   1.0000
   2.250   0.6838   0.02394   0.01456  -0.0925   0.7525   1.0000
   2.500   0.7248   0.02372   0.01407  -0.0931   0.7316   1.0000
   2.750   0.7534   0.02404   0.01421  -0.0925   0.7087   1.0000
   3.000   0.7853   0.02425   0.01422  -0.0922   0.6887   1.0000
   3.250   0.8176   0.02444   0.01422  -0.0919   0.6699   1.0000
   3.500   0.8421   0.02496   0.01462  -0.0907   0.6492   1.0000
   3.750   0.8678   0.02543   0.01497  -0.0896   0.6296   1.0000
   4.000   0.8938   0.02596   0.01541  -0.0887   0.6117   1.0000
   4.250   0.9186   0.02667   0.01606  -0.0878   0.5958   1.0000
   4.500   0.9423   0.02751   0.01688  -0.0869   0.5810   1.0000
   4.750   0.9654   0.02838   0.01775  -0.0859   0.5664   1.0000
   5.000   0.9883   0.02928   0.01869  -0.0849   0.5521   1.0000
   5.250   1.0111   0.03024   0.01968  -0.0840   0.5383   1.0000
   5.500   1.0344   0.03123   0.02069  -0.0830   0.5251   1.0000
   5.750   1.0585   0.03217   0.02166  -0.0821   0.5117   1.0000
   6.000   1.0810   0.03312   0.02267  -0.0810   0.4967   1.0000
   6.250   1.1013   0.03411   0.02372  -0.0795   0.4806   1.0000
   6.500   1.1212   0.03513   0.02482  -0.0780   0.4644   1.0000
   6.750   1.1403   0.03616   0.02593  -0.0764   0.4478   1.0000
   7.000   1.1588   0.03710   0.02697  -0.0746   0.4301   1.0000
   7.250   1.1786   0.03787   0.02780  -0.0729   0.4122   1.0000
   7.500   1.1988   0.03871   0.02870  -0.0713   0.3952   1.0000
   7.750   1.2175   0.03986   0.02994  -0.0697   0.3796   1.0000
   8.000   1.2351   0.04118   0.03142  -0.0680   0.3642   1.0000
   8.250   1.2532   0.04236   0.03270  -0.0663   0.3476   1.0000
   8.500   1.2743   0.04324   0.03359  -0.0647   0.3293   1.0000
   8.750   1.2975   0.04405   0.03433  -0.0633   0.3107   1.0000
   9.000   1.3081   0.04596   0.03647  -0.0610   0.2942   1.0000
   9.250   1.3221   0.04780   0.03843  -0.0590   0.2794   1.0000
   9.500   1.3241   0.05046   0.04141  -0.0563   0.2673   1.0000
   9.750   1.3178   0.05391   0.04519  -0.0533   0.2583   1.0000
  10.000   1.3363   0.05535   0.04668  -0.0519   0.2480   1.0000
  10.250   1.3100   0.06044   0.05217  -0.0482   0.2435   1.0000
  10.500   1.3449   0.06126   0.05300  -0.0480   0.2352   1.0000
  10.750   1.3039   0.06760   0.05965  -0.0444   0.2342   1.0000
  11.000   1.2508   0.07471   0.06689  -0.0413   0.2346   1.0000
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