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GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 274 (DAIMLER V) AIRFOIL (goe274-il)
Reynolds number: 100,000
Max Cl/Cd: 55.76 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe274-il-100000.txt
Download as CSV file: xf-goe274-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 274 (DAIMLER V) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3300   0.10325   0.09846  -0.0244   1.0000   0.0538
  -7.750  -0.3415   0.10221   0.09752  -0.0229   1.0000   0.0547
  -7.500  -0.3521   0.10126   0.09667  -0.0234   1.0000   0.0554
  -7.250  -0.3570   0.10019   0.09566  -0.0276   1.0000   0.0559
  -7.000  -0.3540   0.09854   0.09399  -0.0335   1.0000   0.0562
  -6.750  -0.3539   0.09309   0.08865  -0.0275   1.0000   0.0570
  -6.500  -0.3517   0.08957   0.08517  -0.0233   1.0000   0.0581
  -6.250  -0.3488   0.08678   0.08242  -0.0221   1.0000   0.0594
  -6.000  -0.3446   0.08408   0.07974  -0.0222   1.0000   0.0611
  -5.750  -0.3380   0.08129   0.07696  -0.0235   1.0000   0.0631
  -5.500  -0.3244   0.07844   0.07407  -0.0279   1.0000   0.0663
  -5.250  -0.2991   0.07473   0.07020  -0.0372   1.0000   0.0691
  -5.000  -0.2984   0.07143   0.06702  -0.0331   1.0000   0.0708
  -4.750  -0.2891   0.06873   0.06433  -0.0325   1.0000   0.0735
  -4.500  -0.2407   0.06731   0.06238  -0.0448   1.0000   0.0819
  -4.250  -0.2348   0.06220   0.05745  -0.0434   1.0000   0.0833
  -4.000  -0.2264   0.05924   0.05459  -0.0417   1.0000   0.0858
  -3.750  -0.2075   0.05678   0.05208  -0.0429   1.0000   0.0912
  -3.500  -0.1752   0.05369   0.04875  -0.0480   1.0000   0.0991
  -3.250  -0.1593   0.05146   0.04656  -0.0479   1.0000   0.1057
  -3.000  -0.1312   0.04885   0.04379  -0.0511   1.0000   0.1162
  -2.750  -0.0864   0.04596   0.04072  -0.0571   0.9957   0.1312
  -2.500  -0.0369   0.04316   0.03778  -0.0635   0.9885   0.1513
  -2.250   0.0136   0.04045   0.03492  -0.0701   0.9819   0.1813
  -2.000   0.0591   0.03829   0.03269  -0.0753   0.9735   0.2321
  -1.750   0.0958   0.03641   0.03093  -0.0781   0.9648   0.3130
  -1.500   0.1296   0.03370   0.02854  -0.0791   0.9579   0.3957
  -1.250   0.1583   0.03154   0.02661  -0.0781   0.9475   0.4763
  -1.000   0.2019   0.02920   0.02438  -0.0800   0.9400   0.5412
  -0.750   0.3374   0.02770   0.02037  -0.1025   0.9303   0.2198
  -0.500   0.3909   0.02632   0.01839  -0.1048   0.9190   0.1551
  -0.250   0.4463   0.02487   0.01651  -0.1080   0.9102   0.1256
   0.000   0.4978   0.02356   0.01492  -0.1110   0.8993   0.1119
   0.250   0.5426   0.02173   0.01315  -0.1132   0.8860   0.1069
   0.500   0.5860   0.02031   0.01170  -0.1147   0.8710   0.1030
   0.750   0.6277   0.01897   0.01039  -0.1159   0.8535   0.1040
   1.000   0.6621   0.01794   0.00938  -0.1158   0.8267   0.1073
   1.250   0.6974   0.01705   0.00838  -0.1157   0.7952   0.1085
   1.500   0.7300   0.01654   0.00763  -0.1153   0.7565   0.1113
   1.750   0.7606   0.01625   0.00705  -0.1147   0.7166   0.1180
   2.000   0.7881   0.01623   0.00682  -0.1138   0.6773   0.1350
   2.250   0.8060   0.01460   0.00676  -0.1111   0.6476   1.0000
   2.500   0.8328   0.01499   0.00674  -0.1103   0.6206   1.0000
   2.750   0.8594   0.01542   0.00685  -0.1097   0.5973   1.0000
   3.000   0.8860   0.01589   0.00703  -0.1093   0.5771   1.0000
   3.250   0.9123   0.01637   0.00731  -0.1089   0.5580   1.0000
   3.500   0.9386   0.01688   0.00763  -0.1085   0.5403   1.0000
   3.750   0.9647   0.01741   0.00801  -0.1081   0.5234   1.0000
   4.000   0.9906   0.01794   0.00841  -0.1077   0.5072   1.0000
   4.250   1.0163   0.01847   0.00884  -0.1073   0.4912   1.0000
   4.500   1.0418   0.01901   0.00929  -0.1069   0.4756   1.0000
   4.750   1.0671   0.01955   0.00979  -0.1064   0.4603   1.0000
   5.000   1.0921   0.02009   0.01030  -0.1059   0.4451   1.0000
   5.250   1.1170   0.02065   0.01082  -0.1054   0.4300   1.0000
   5.500   1.1416   0.02123   0.01139  -0.1048   0.4149   1.0000
   5.750   1.1660   0.02182   0.01197  -0.1042   0.3999   1.0000
   6.000   1.1901   0.02243   0.01256  -0.1036   0.3854   1.0000
   6.250   1.2142   0.02305   0.01317  -0.1029   0.3715   1.0000
   6.500   1.2383   0.02366   0.01377  -0.1023   0.3587   1.0000
   6.750   1.2631   0.02426   0.01429  -0.1019   0.3472   1.0000
   7.000   1.2858   0.02489   0.01507  -0.1011   0.3356   1.0000
   7.250   1.3096   0.02563   0.01589  -0.1005   0.3261   1.0000
   7.500   1.3349   0.02631   0.01657  -0.1002   0.3180   1.0000
   7.750   1.3562   0.02694   0.01739  -0.0992   0.3078   1.0000
   8.000   1.3769   0.02729   0.01779  -0.0980   0.2959   1.0000
   8.250   1.3973   0.02760   0.01810  -0.0969   0.2841   1.0000
   8.500   1.4177   0.02799   0.01858  -0.0957   0.2737   1.0000
   8.750   1.4357   0.02843   0.01921  -0.0942   0.2626   1.0000
   9.000   1.4539   0.02886   0.01975  -0.0928   0.2523   1.0000
   9.250   1.4717   0.02924   0.02015  -0.0913   0.2419   1.0000
   9.500   1.4865   0.02962   0.02075  -0.0892   0.2305   1.0000
   9.750   1.5005   0.03008   0.02142  -0.0871   0.2192   1.0000
  10.000   1.5103   0.03045   0.02193  -0.0844   0.2044   1.0000
  10.250   1.5198   0.03100   0.02262  -0.0817   0.1898   1.0000
  10.500   1.5257   0.03175   0.02345  -0.0785   0.1724   1.0000
  10.750   1.5311   0.03265   0.02454  -0.0752   0.1501   1.0000
  11.000   1.5320   0.03412   0.02593  -0.0717   0.1009   1.0000
  11.250   1.5196   0.03692   0.02837  -0.0673   0.0770   1.0000
  11.500   1.5111   0.03966   0.03113  -0.0637   0.0643   1.0000
  11.750   1.5033   0.04248   0.03401  -0.0606   0.0574   1.0000
  12.000   1.4970   0.04531   0.03698  -0.0581   0.0532   1.0000
  12.250   1.4873   0.04866   0.04044  -0.0562   0.0507   1.0000
  12.500   1.4754   0.05249   0.04440  -0.0548   0.0493   1.0000
  12.750   1.4652   0.05647   0.04859  -0.0540   0.0481   1.0000
  13.000   1.4534   0.06095   0.05326  -0.0539   0.0472   1.0000
  13.250   1.4411   0.06585   0.05835  -0.0545   0.0465   1.0000
  13.500   1.4285   0.07105   0.06372  -0.0554   0.0459   1.0000
  13.750   1.4165   0.07635   0.06919  -0.0567   0.0453   1.0000
  14.000   1.4058   0.08154   0.07452  -0.0579   0.0447   1.0000
  14.250   1.3971   0.08636   0.07947  -0.0589   0.0441   1.0000
  14.500   1.3909   0.09069   0.08390  -0.0595   0.0434   1.0000
  14.750   1.3877   0.09437   0.08762  -0.0596   0.0425   1.0000
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