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GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 276 (DAIMLER VII) AIRFOIL (goe276-il)
Reynolds number: 100,000
Max Cl/Cd: 53.05 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe276-il-100000.txt
Download as CSV file: xf-goe276-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3792   0.09699   0.09211  -0.0188   1.0000   0.0549
  -7.500  -0.3786   0.09438   0.08958  -0.0193   1.0000   0.0569
  -7.250  -0.3756   0.09169   0.08695  -0.0215   1.0000   0.0592
  -7.000  -0.3695   0.08966   0.08495  -0.0286   1.0000   0.0614
  -6.750  -0.3537   0.08791   0.08309  -0.0398   1.0000   0.0622
  -6.500  -0.3526   0.08199   0.07731  -0.0356   1.0000   0.0633
  -6.250  -0.3493   0.07831   0.07371  -0.0313   1.0000   0.0650
  -6.000  -0.3419   0.07526   0.07069  -0.0307   1.0000   0.0672
  -5.750  -0.3319   0.07220   0.06763  -0.0321   1.0000   0.0702
  -5.500  -0.2971   0.07010   0.06515  -0.0446   1.0000   0.0761
  -5.250  -0.2922   0.06509   0.06027  -0.0431   1.0000   0.0775
  -5.000  -0.2896   0.06203   0.05733  -0.0395   1.0000   0.0801
  -4.750  -0.2750   0.05934   0.05460  -0.0402   1.0000   0.0864
  -4.500  -0.2500   0.05561   0.05065  -0.0448   1.0000   0.0928
  -4.250  -0.2380   0.05295   0.04801  -0.0437   1.0000   0.0974
  -4.000  -0.2100   0.04969   0.04450  -0.0476   1.0000   0.1071
  -3.750  -0.1937   0.04725   0.04206  -0.0473   1.0000   0.1148
  -3.500  -0.1717   0.04444   0.03913  -0.0487   1.0000   0.1257
  -3.250  -0.1441   0.04240   0.03679  -0.0513   1.0000   0.1502
  -3.000  -0.1263   0.03988   0.03431  -0.0512   1.0000   0.1671
  -2.750  -0.1043   0.03804   0.03238  -0.0518   1.0000   0.1960
  -2.500  -0.0855   0.03610   0.03050  -0.0515   1.0000   0.2274
  -1.750  -0.0382   0.03142   0.02623  -0.0465   1.0000   0.4049
  -1.500  -0.0247   0.02954   0.02460  -0.0431   1.0000   0.4683
  -1.250  -0.0031   0.02784   0.02300  -0.0416   1.0000   0.5254
  -0.750   0.1861   0.02411   0.01578  -0.0666   0.9886   0.1290
  -0.500   0.2399   0.02294   0.01426  -0.0707   0.9801   0.1149
  -0.250   0.2943   0.02207   0.01307  -0.0750   0.9705   0.1055
   0.000   0.3457   0.02085   0.01183  -0.0792   0.9594   0.1032
   0.250   0.3963   0.01970   0.01072  -0.0831   0.9466   0.1032
   0.500   0.4482   0.01839   0.00959  -0.0872   0.9333   0.1098
   0.750   0.5017   0.01724   0.00847  -0.0912   0.9185   0.1147
   1.000   0.5491   0.01629   0.00749  -0.0937   0.8976   0.1241
   1.250   0.5905   0.01414   0.00689  -0.0955   0.8735   0.6464
   1.500   0.6181   0.01327   0.00625  -0.0931   0.8355   1.0000
   1.750   0.6464   0.01316   0.00583  -0.0917   0.7885   1.0000
   2.000   0.6727   0.01318   0.00556  -0.0903   0.7348   1.0000
   2.250   0.6988   0.01337   0.00538  -0.0891   0.6860   1.0000
   2.500   0.7249   0.01372   0.00538  -0.0881   0.6483   1.0000
   2.750   0.7511   0.01417   0.00554  -0.0875   0.6191   1.0000
   3.000   0.7774   0.01466   0.00582  -0.0870   0.5954   1.0000
   3.250   0.8037   0.01515   0.00615  -0.0866   0.5736   1.0000
   3.500   0.8299   0.01565   0.00649  -0.0861   0.5533   1.0000
   3.750   0.8560   0.01616   0.00685  -0.0857   0.5348   1.0000
   4.000   0.8819   0.01665   0.00729  -0.0852   0.5160   1.0000
   4.250   0.9075   0.01716   0.00773  -0.0848   0.4976   1.0000
   4.500   0.9333   0.01770   0.00820  -0.0843   0.4807   1.0000
   4.750   0.9592   0.01828   0.00873  -0.0840   0.4650   1.0000
   5.000   0.9850   0.01888   0.00934  -0.0836   0.4498   1.0000
   5.250   1.0105   0.01950   0.00996  -0.0832   0.4347   1.0000
   5.500   1.0360   0.02013   0.01061  -0.0828   0.4197   1.0000
   5.750   1.0612   0.02076   0.01133  -0.0823   0.4051   1.0000
   6.000   1.0862   0.02139   0.01203  -0.0818   0.3905   1.0000
   6.250   1.1109   0.02199   0.01273  -0.0812   0.3758   1.0000
   6.500   1.1353   0.02257   0.01340  -0.0806   0.3609   1.0000
   6.750   1.1594   0.02312   0.01409  -0.0799   0.3457   1.0000
   7.000   1.1829   0.02348   0.01451  -0.0790   0.3291   1.0000
   7.250   1.2045   0.02360   0.01471  -0.0778   0.3094   1.0000
   7.500   1.2252   0.02367   0.01488  -0.0765   0.2887   1.0000
   7.750   1.2454   0.02383   0.01505  -0.0752   0.2686   1.0000
   8.000   1.2641   0.02402   0.01539  -0.0738   0.2447   1.0000
   8.250   1.2826   0.02435   0.01585  -0.0724   0.2195   1.0000
   8.500   1.2999   0.02476   0.01635  -0.0708   0.1801   1.0000
   8.750   1.3056   0.02713   0.01813  -0.0679   0.0933   1.0000
   9.000   1.3133   0.02943   0.02011  -0.0651   0.0677   1.0000
   9.250   1.3216   0.03138   0.02211  -0.0624   0.0587   1.0000
   9.500   1.3281   0.03338   0.02423  -0.0594   0.0539   1.0000
   9.750   1.3354   0.03527   0.02626  -0.0566   0.0509   1.0000
  10.000   1.3418   0.03732   0.02836  -0.0537   0.0485   1.0000
  10.250   1.3499   0.03992   0.03094  -0.0512   0.0466   1.0000
  10.500   1.3652   0.04255   0.03370  -0.0495   0.0452   1.0000
  10.750   1.3769   0.04477   0.03618  -0.0475   0.0435   1.0000
  11.000   1.3862   0.04716   0.03882  -0.0453   0.0418   1.0000
  11.250   1.3950   0.04989   0.04182  -0.0433   0.0407   1.0000
  11.500   1.4007   0.05297   0.04518  -0.0410   0.0402   1.0000
  11.750   1.4009   0.05622   0.04874  -0.0384   0.0400   1.0000
  12.000   1.3955   0.05968   0.05253  -0.0357   0.0400   1.0000
  12.250   1.3845   0.06342   0.05661  -0.0332   0.0402   1.0000
  12.500   1.3694   0.06755   0.06108  -0.0315   0.0404   1.0000
  12.750   1.3510   0.07219   0.06603  -0.0306   0.0406   1.0000
  13.000   1.3301   0.07742   0.07156  -0.0309   0.0409   1.0000
  13.250   1.3071   0.08338   0.07780  -0.0324   0.0413   1.0000
  13.500   1.2825   0.09023   0.08491  -0.0355   0.0416   1.0000
  13.750   1.2562   0.09812   0.09303  -0.0400   0.0421   1.0000
  14.000   1.2284   0.10719   0.10231  -0.0460   0.0425   1.0000
  14.250   1.1987   0.11751   0.11280  -0.0531   0.0431   1.0000
  14.500   1.1679   0.12909   0.12447  -0.0611   0.0439   1.0000
  14.750   1.1396   0.14122   0.13666  -0.0690   0.0448   1.0000
  15.000   1.1211   0.15153   0.14697  -0.0747   0.0457   1.0000
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