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GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 274 (DAIMLER V) AIRFOIL (goe274-il)
Reynolds number: 500,000
Max Cl/Cd: 92.3 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe274-il-500000-n5.txt
Download as CSV file: xf-goe274-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3325   0.11141   0.10910  -0.0261   1.0000   0.0110
  -9.500  -0.3321   0.10924   0.10696  -0.0255   1.0000   0.0112
  -9.250  -0.3339   0.10688   0.10463  -0.0246   1.0000   0.0114
  -9.000  -0.3246   0.10324   0.10099  -0.0272   0.9987   0.0115
  -8.750  -0.3118   0.09925   0.09700  -0.0309   0.9967   0.0118
  -8.500  -0.2977   0.09508   0.09283  -0.0352   0.9946   0.0121
  -8.250  -0.2903   0.08919   0.08694  -0.0409   0.9901   0.0131
  -8.000  -0.2715   0.08663   0.08438  -0.0441   0.9873   0.0134
  -7.750  -0.2526   0.08362   0.08137  -0.0483   0.9848   0.0140
  -7.500  -0.2362   0.07982   0.07757  -0.0531   0.9798   0.0144
  -7.250  -0.2152   0.07541   0.07314  -0.0597   0.9764   0.0147
  -7.000  -0.1944   0.07099   0.06870  -0.0661   0.9716   0.0151
  -6.750  -0.1696   0.06505   0.06271  -0.0754   0.9657   0.0164
  -6.500  -0.1458   0.06289   0.06053  -0.0785   0.9625   0.0171
  -6.250  -0.1244   0.05966   0.05726  -0.0825   0.9552   0.0179
  -6.000  -0.0966   0.05527   0.05279  -0.0887   0.9500   0.0182
  -5.750  -0.0701   0.05108   0.04851  -0.0937   0.9431   0.0186
  -5.250  -0.0054   0.04460   0.04177  -0.1027   0.9297   0.0241
  -5.000   0.0264   0.04065   0.03761  -0.1064   0.9221   0.0242
  -4.750   0.0552   0.03722   0.03400  -0.1088   0.9142   0.0243
  -4.500   0.0857   0.03409   0.03063  -0.1107   0.9051   0.0244
  -4.250   0.1151   0.03136   0.02766  -0.1121   0.8945   0.0245
  -4.000   0.1438   0.02784   0.02387  -0.1137   0.8837   0.0247
  -3.750   0.1702   0.02541   0.02128  -0.1149   0.8725   0.0251
  -3.500   0.1965   0.02416   0.01994  -0.1156   0.8592   0.0256
  -3.250   0.2249   0.02263   0.01821  -0.1162   0.8439   0.0259
  -3.000   0.2532   0.02253   0.01795  -0.1160   0.8256   0.0300
  -2.750   0.2833   0.02193   0.01698  -0.1158   0.8024   0.0307
  -2.500   0.3104   0.01873   0.01353  -0.1171   0.7742   0.0274
  -2.250   0.3393   0.01724   0.01161  -0.1170   0.7372   0.0266
  -2.000   0.3667   0.01633   0.01030  -0.1168   0.6911   0.0266
  -1.750   0.3935   0.01566   0.00921  -0.1165   0.6352   0.0267
  -1.500   0.4196   0.01524   0.00838  -0.1161   0.5764   0.0269
  -1.250   0.4464   0.01492   0.00776  -0.1160   0.5387   0.0276
  -1.000   0.4744   0.01439   0.00699  -0.1160   0.5152   0.0275
  -0.750   0.5025   0.01386   0.00626  -0.1160   0.4965   0.0272
  -0.500   0.5304   0.01344   0.00566  -0.1159   0.4775   0.0272
  -0.250   0.5581   0.01312   0.00517  -0.1159   0.4594   0.0274
   0.000   0.5860   0.01283   0.00478  -0.1159   0.4452   0.0278
   0.250   0.6140   0.01258   0.00445  -0.1159   0.4333   0.0282
   0.500   0.6418   0.01240   0.00419  -0.1159   0.4208   0.0287
   0.750   0.6695   0.01226   0.00398  -0.1159   0.4083   0.0291
   1.000   0.6971   0.01220   0.00385  -0.1159   0.3970   0.0298
   1.250   0.7248   0.01220   0.00380  -0.1159   0.3847   0.0305
   1.500   0.7524   0.01214   0.00369  -0.1159   0.3724   0.0307
   1.750   0.7801   0.01209   0.00359  -0.1159   0.3599   0.0308
   2.000   0.8079   0.01200   0.00346  -0.1160   0.3483   0.0312
   2.250   0.8359   0.01193   0.00337  -0.1162   0.3384   0.0320
   2.500   0.8635   0.01195   0.00336  -0.1162   0.3291   0.0331
   3.000   0.9182   0.01211   0.00346  -0.1162   0.3090   0.0355
   3.250   0.9452   0.01224   0.00355  -0.1161   0.2987   0.0375
   3.500   0.9720   0.01240   0.00366  -0.1160   0.2876   0.0393
   3.750   0.9988   0.01254   0.00376  -0.1158   0.2757   0.0420
   4.000   1.0254   0.01272   0.00389  -0.1157   0.2628   0.0486
   4.500   1.0707   0.01160   0.00442  -0.1141   0.2354   1.0000
   4.750   1.0965   0.01191   0.00464  -0.1138   0.2205   1.0000
   5.000   1.1220   0.01223   0.00488  -0.1136   0.2067   1.0000
   5.250   1.1476   0.01254   0.00513  -0.1133   0.1968   1.0000
   5.500   1.1728   0.01288   0.00541  -0.1129   0.1865   1.0000
   5.750   1.1982   0.01319   0.00568  -0.1126   0.1786   1.0000
   6.000   1.2232   0.01352   0.00598  -0.1123   0.1708   1.0000
   6.250   1.2481   0.01386   0.00628  -0.1119   0.1627   1.0000
   6.500   1.2729   0.01419   0.00659  -0.1115   0.1564   1.0000
   6.750   1.2978   0.01449   0.00691  -0.1111   0.1486   1.0000
   7.000   1.3221   0.01485   0.00724  -0.1106   0.1406   1.0000
   7.250   1.3458   0.01525   0.00759  -0.1101   0.1265   1.0000
   7.500   1.3634   0.01631   0.00832  -0.1087   0.0812   1.0000
   7.750   1.3841   0.01698   0.00895  -0.1077   0.0661   1.0000
   8.000   1.3971   0.01844   0.01015  -0.1055   0.0198   1.0000
   8.250   1.4177   0.01905   0.01079  -0.1044   0.0165   1.0000
   8.500   1.4383   0.01961   0.01142  -0.1033   0.0146   1.0000
   8.750   1.4587   0.02015   0.01203  -0.1022   0.0134   1.0000
   9.000   1.4779   0.02076   0.01272  -0.1009   0.0124   1.0000
   9.250   1.4954   0.02149   0.01352  -0.0993   0.0115   1.0000
   9.500   1.5112   0.02228   0.01442  -0.0975   0.0108   1.0000
   9.750   1.5278   0.02294   0.01515  -0.0958   0.0103   1.0000
  10.000   1.5427   0.02367   0.01597  -0.0938   0.0098   1.0000
  10.250   1.5546   0.02442   0.01681  -0.0914   0.0093   1.0000
  10.500   1.5656   0.02527   0.01773  -0.0888   0.0088   1.0000
  10.750   1.5752   0.02623   0.01877  -0.0863   0.0084   1.0000
  11.000   1.5820   0.02743   0.02006  -0.0834   0.0081   1.0000
  11.250   1.5848   0.02895   0.02170  -0.0802   0.0078   1.0000
  11.500   1.5922   0.03018   0.02304  -0.0778   0.0076   1.0000
  11.750   1.5979   0.03157   0.02455  -0.0753   0.0075   1.0000
  12.000   1.6019   0.03317   0.02627  -0.0729   0.0073   1.0000
  12.250   1.6043   0.03497   0.02819  -0.0706   0.0071   1.0000
  12.500   1.6054   0.03698   0.03032  -0.0685   0.0069   1.0000
  12.750   1.6056   0.03920   0.03267  -0.0666   0.0067   1.0000
  13.000   1.6048   0.04168   0.03527  -0.0651   0.0065   1.0000
  13.250   1.6032   0.04439   0.03810  -0.0639   0.0064   1.0000
  13.500   1.6002   0.04747   0.04130  -0.0631   0.0062   1.0000
  13.750   1.5956   0.05095   0.04491  -0.0627   0.0061   1.0000
  14.000   1.5895   0.05487   0.04896  -0.0628   0.0060   1.0000
  14.250   1.5808   0.05943   0.05366  -0.0635   0.0059   1.0000
  14.500   1.5702   0.06464   0.05901  -0.0647   0.0058   1.0000
  14.750   1.5575   0.07043   0.06495  -0.0664   0.0058   1.0000
  15.000   1.5429   0.07666   0.07133  -0.0684   0.0057   1.0000
  15.250   1.5266   0.08319   0.07799  -0.0705   0.0057   1.0000
  15.500   1.5089   0.08992   0.08486  -0.0727   0.0056   1.0000
  15.750   1.4921   0.09652   0.09159  -0.0748   0.0056   1.0000
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