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GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 275 (DAIMLER VI) AIRFOIL (goe275-il)
Reynolds number: 50,000
Max Cl/Cd: 40.19 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe275-il-50000-n5.txt
Download as CSV file: xf-goe275-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3216   0.09916   0.09263  -0.0236   1.0000   0.0858
  -7.250  -0.3300   0.09796   0.09156  -0.0242   1.0000   0.0886
  -7.000  -0.3376   0.09727   0.09098  -0.0279   1.0000   0.0900
  -6.750  -0.3310   0.09256   0.08636  -0.0236   1.0000   0.0933
  -6.500  -0.3286   0.08996   0.08382  -0.0221   1.0000   0.0982
  -6.250  -0.3308   0.08860   0.08252  -0.0256   1.0000   0.1038
  -5.750  -0.3252   0.08251   0.07656  -0.0229   1.0000   0.1107
  -5.500  -0.3180   0.08085   0.07485  -0.0283   1.0000   0.1192
  -5.250  -0.3141   0.07725   0.07134  -0.0266   1.0000   0.1223
  -5.000  -0.3086   0.07454   0.06868  -0.0247   1.0000   0.1285
  -4.750  -0.2971   0.07175   0.06585  -0.0282   1.0000   0.1375
  -4.500  -0.2829   0.06945   0.06346  -0.0313   1.0000   0.1513
  -4.250  -0.2799   0.06644   0.06059  -0.0272   1.0000   0.1596
  -4.000  -0.2686   0.06378   0.05793  -0.0278   1.0000   0.1742
  -3.500  -0.2317   0.05814   0.05224  -0.0312   0.9957   0.2185
  -2.500  -0.0093   0.04180   0.03383  -0.0632   0.9642   0.1024
  -2.250   0.0420   0.03879   0.03021  -0.0678   0.9525   0.0887
  -2.000   0.0876   0.03621   0.02730  -0.0715   0.9392   0.0869
  -1.750   0.1323   0.03390   0.02456  -0.0746   0.9256   0.0825
  -1.500   0.1766   0.03212   0.02217  -0.0768   0.9126   0.0777
  -1.250   0.2174   0.03081   0.02043  -0.0786   0.9009   0.0758
  -1.000   0.2610   0.02929   0.01861  -0.0811   0.8915   0.0769
  -0.750   0.2967   0.02801   0.01716  -0.0822   0.8783   0.0779
  -0.500   0.3332   0.02701   0.01593  -0.0831   0.8649   0.0773
  -0.250   0.3695   0.02605   0.01481  -0.0838   0.8508   0.0770
   0.000   0.4063   0.02517   0.01376  -0.0846   0.8360   0.0772
   0.250   0.4412   0.02435   0.01284  -0.0850   0.8195   0.0779
   0.500   0.4749   0.02361   0.01204  -0.0854   0.8017   0.0810
   0.750   0.5091   0.02297   0.01132  -0.0857   0.7829   0.0850
   1.000   0.5392   0.02254   0.01079  -0.0854   0.7601   0.0872
   1.250   0.5729   0.02210   0.01020  -0.0856   0.7378   0.0897
   1.500   0.6048   0.02173   0.00974  -0.0856   0.7128   0.0937
   1.750   0.6386   0.02142   0.00930  -0.0859   0.6886   0.1016
   2.000   0.6697   0.02109   0.00914  -0.0859   0.6629   0.1456
   2.500   0.7296   0.01981   0.00898  -0.0854   0.6147   1.0000
   2.750   0.7572   0.02018   0.00906  -0.0849   0.5929   1.0000
   3.000   0.7835   0.02062   0.00926  -0.0843   0.5724   1.0000
   3.250   0.8096   0.02107   0.00951  -0.0837   0.5534   1.0000
   3.500   0.8354   0.02154   0.00980  -0.0831   0.5354   1.0000
   3.750   0.8607   0.02201   0.01011  -0.0825   0.5184   1.0000
   4.000   0.8855   0.02249   0.01045  -0.0818   0.5019   1.0000
   4.250   0.9099   0.02297   0.01084  -0.0810   0.4858   1.0000
   4.500   0.9339   0.02346   0.01124  -0.0803   0.4707   1.0000
   4.750   0.9580   0.02399   0.01173  -0.0796   0.4572   1.0000
   5.000   0.9827   0.02454   0.01230  -0.0790   0.4457   1.0000
   5.250   1.0078   0.02510   0.01282  -0.0785   0.4351   1.0000
   5.500   1.0321   0.02568   0.01342  -0.0779   0.4242   1.0000
   5.750   1.0556   0.02632   0.01412  -0.0772   0.4134   1.0000
   6.000   1.0797   0.02694   0.01479  -0.0766   0.4032   1.0000
   6.250   1.1032   0.02756   0.01544  -0.0758   0.3923   1.0000
   6.500   1.1246   0.02824   0.01623  -0.0748   0.3802   1.0000
   6.750   1.1459   0.02891   0.01700  -0.0738   0.3679   1.0000
   7.000   1.1670   0.02956   0.01769  -0.0727   0.3553   1.0000
   7.250   1.1883   0.03019   0.01831  -0.0716   0.3429   1.0000
   7.500   1.2065   0.03093   0.01923  -0.0702   0.3297   1.0000
   7.750   1.2240   0.03167   0.02013  -0.0687   0.3163   1.0000
   8.000   1.2410   0.03240   0.02100  -0.0671   0.3029   1.0000
   8.250   1.2580   0.03315   0.02188  -0.0655   0.2903   1.0000
   8.500   1.2752   0.03390   0.02273  -0.0640   0.2787   1.0000
   8.750   1.2899   0.03477   0.02385  -0.0622   0.2663   1.0000
   9.000   1.3032   0.03569   0.02498  -0.0603   0.2536   1.0000
   9.250   1.3153   0.03661   0.02608  -0.0583   0.2409   1.0000
   9.500   1.3262   0.03758   0.02720  -0.0561   0.2283   1.0000
   9.750   1.3359   0.03862   0.02837  -0.0539   0.2163   1.0000
  10.000   1.3452   0.03976   0.02962  -0.0517   0.2057   1.0000
  10.250   1.3538   0.04092   0.03081  -0.0494   0.1966   1.0000
  10.500   1.3602   0.04252   0.03257  -0.0471   0.1874   1.0000
  10.750   1.3686   0.04396   0.03399  -0.0450   0.1800   1.0000
  11.000   1.3732   0.04587   0.03611  -0.0428   0.1723   1.0000
  11.250   1.3839   0.04737   0.03757  -0.0412   0.1660   1.0000
  11.500   1.3833   0.04983   0.04039  -0.0391   0.1601   1.0000
  11.750   1.3882   0.05196   0.04269  -0.0374   0.1551   1.0000
  12.000   1.4043   0.05363   0.04434  -0.0364   0.1506   1.0000
  12.250   1.3955   0.05692   0.04805  -0.0345   0.1474   1.0000
  12.500   1.3867   0.06035   0.05180  -0.0331   0.1440   1.0000
  12.750   1.3803   0.06366   0.05534  -0.0322   0.1407   1.0000
  13.000   1.3957   0.06498   0.05665  -0.0312   0.1360   1.0000
  13.250   1.3704   0.07039   0.06243  -0.0312   0.1342   1.0000
  13.500   1.3415   0.07699   0.06931  -0.0325   0.1330   1.0000
  13.750   1.3022   0.08601   0.07856  -0.0360   0.1324   1.0000
  14.000   1.2317   0.10230   0.09499  -0.0449   0.1328   1.0000
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