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GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il)
Reynolds number: 200,000
Max Cl/Cd: 77.39 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe282-il-200000.txt
Download as CSV file: xf-goe282-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 282 (DAIMLER XIII) AIRFOIL                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3487   0.09421   0.09107  -0.0215   1.0000   0.0462
  -7.250  -0.3610   0.09278   0.08971  -0.0188   1.0000   0.0468
  -7.000  -0.3680   0.09076   0.08775  -0.0177   1.0000   0.0478
  -6.750  -0.3734   0.08850   0.08554  -0.0173   1.0000   0.0490
  -6.500  -0.3773   0.08597   0.08305  -0.0182   1.0000   0.0505
  -6.250  -0.3282   0.07836   0.07528  -0.0427   0.9945   0.0534
  -6.000  -0.3189   0.07266   0.06963  -0.0419   0.9911   0.0550
  -5.750  -0.2946   0.06983   0.06679  -0.0431   0.9871   0.0571
  -5.500  -0.2347   0.06107   0.05772  -0.0637   0.9815   0.0666
  -5.250  -0.2168   0.05875   0.05547  -0.0623   0.9766   0.0686
  -5.000  -0.1603   0.05211   0.04844  -0.0762   0.9724   0.0795
  -4.750  -0.1368   0.04971   0.04613  -0.0764   0.9681   0.0816
  -4.500  -0.0939   0.04544   0.04159  -0.0835   0.9622   0.0935
  -4.250  -0.0396   0.03048   0.02558  -0.0942   0.9603   0.0638
  -4.000   0.0052   0.02452   0.01877  -0.0992   0.9585   0.0631
  -3.750   0.0460   0.02144   0.01504  -0.1020   0.9549   0.0636
  -3.500   0.0834   0.02017   0.01334  -0.1037   0.9487   0.0659
  -3.250   0.1257   0.01808   0.01095  -0.1067   0.9458   0.0680
  -3.000   0.1704   0.01700   0.00981  -0.1100   0.9434   0.0716
  -2.750   0.2050   0.01630   0.00901  -0.1111   0.9354   0.0759
  -2.500   0.2476   0.01534   0.00797  -0.1137   0.9315   0.0797
  -2.250   0.2885   0.01456   0.00724  -0.1160   0.9272   0.0867
  -2.000   0.3217   0.01401   0.00674  -0.1167   0.9178   0.0979
  -1.750   0.3572   0.01351   0.00634  -0.1176   0.9095   0.1259
  -1.500   0.3925   0.01327   0.00610  -0.1185   0.8999   0.1686
  -1.250   0.4227   0.01307   0.00586  -0.1184   0.8860   0.1882
  -1.000   0.4523   0.01282   0.00556  -0.1181   0.8704   0.2035
  -0.750   0.4799   0.01257   0.00529  -0.1175   0.8510   0.2166
  -0.500   0.5076   0.01231   0.00498  -0.1169   0.8290   0.2288
  -0.250   0.5352   0.01210   0.00472  -0.1164   0.8057   0.2437
   0.000   0.5630   0.01192   0.00446  -0.1159   0.7834   0.2565
   0.250   0.5905   0.01181   0.00427  -0.1155   0.7610   0.2680
   0.500   0.6178   0.01171   0.00411  -0.1151   0.7391   0.2830
   0.750   0.6446   0.01161   0.00402  -0.1147   0.7178   0.3050
   1.000   0.6695   0.01094   0.00405  -0.1143   0.6980   0.5450
   1.250   0.6925   0.01019   0.00394  -0.1124   0.6800   1.0000
   1.500   0.7193   0.01041   0.00397  -0.1120   0.6628   1.0000
   1.750   0.7461   0.01062   0.00402  -0.1116   0.6463   1.0000
   2.000   0.7727   0.01082   0.00410  -0.1112   0.6303   1.0000
   2.250   0.7993   0.01103   0.00420  -0.1108   0.6148   1.0000
   2.500   0.8258   0.01125   0.00431  -0.1104   0.5998   1.0000
   2.750   0.8521   0.01148   0.00444  -0.1100   0.5848   1.0000
   3.000   0.8782   0.01172   0.00458  -0.1096   0.5697   1.0000
   3.250   0.9042   0.01198   0.00476  -0.1092   0.5546   1.0000
   3.500   0.9301   0.01225   0.00496  -0.1087   0.5396   1.0000
   3.750   0.9558   0.01253   0.00517  -0.1083   0.5245   1.0000
   4.000   0.9812   0.01281   0.00541  -0.1077   0.5079   1.0000
   4.250   1.0059   0.01308   0.00562  -0.1071   0.4883   1.0000
   4.500   1.0300   0.01337   0.00583  -0.1063   0.4676   1.0000
   4.750   1.0540   0.01362   0.00605  -0.1055   0.4438   1.0000
   5.000   1.0774   0.01394   0.00629  -0.1047   0.4204   1.0000
   5.250   1.1006   0.01428   0.00655  -0.1038   0.3955   1.0000
   5.500   1.1234   0.01468   0.00685  -0.1030   0.3718   1.0000
   5.750   1.1457   0.01513   0.00718  -0.1020   0.3505   1.0000
   6.000   1.1680   0.01559   0.00757  -0.1012   0.3308   1.0000
   6.250   1.1903   0.01605   0.00795  -0.1003   0.3120   1.0000
   6.500   1.2123   0.01652   0.00836  -0.0994   0.2950   1.0000
   6.750   1.2346   0.01697   0.00880  -0.0985   0.2811   1.0000
   7.000   1.2566   0.01743   0.00924  -0.0976   0.2669   1.0000
   7.250   1.2777   0.01791   0.00968  -0.0967   0.2504   1.0000
   7.500   1.2977   0.01845   0.01015  -0.0955   0.2320   1.0000
   7.750   1.3186   0.01894   0.01061  -0.0945   0.2160   1.0000
   8.000   1.3396   0.01940   0.01109  -0.0935   0.1973   1.0000
   8.250   1.3591   0.01998   0.01158  -0.0923   0.1703   1.0000
   8.500   1.3729   0.02101   0.01229  -0.0904   0.1221   1.0000
   8.750   1.3850   0.02219   0.01326  -0.0881   0.0959   1.0000
   9.000   1.3984   0.02320   0.01420  -0.0860   0.0818   1.0000
   9.250   1.4130   0.02404   0.01507  -0.0841   0.0728   1.0000
   9.500   1.4270   0.02478   0.01585  -0.0819   0.0645   1.0000
   9.750   1.4392   0.02564   0.01672  -0.0796   0.0548   1.0000
  10.250   1.4484   0.02851   0.01940  -0.0733   0.0244   1.0000
  10.500   1.4550   0.02984   0.02083  -0.0706   0.0230   1.0000
  10.750   1.4618   0.03121   0.02235  -0.0681   0.0220   1.0000
  11.000   1.4678   0.03268   0.02397  -0.0658   0.0214   1.0000
  11.250   1.4725   0.03432   0.02578  -0.0634   0.0209   1.0000
  11.500   1.4757   0.03615   0.02777  -0.0612   0.0207   1.0000
  11.750   1.4775   0.03819   0.02999  -0.0592   0.0205   1.0000
  12.000   1.4775   0.04051   0.03249  -0.0574   0.0203   1.0000
  12.250   1.4755   0.04316   0.03532  -0.0558   0.0201   1.0000
  12.500   1.4717   0.04616   0.03849  -0.0546   0.0199   1.0000
  12.750   1.4664   0.04952   0.04202  -0.0538   0.0196   1.0000
  13.000   1.4596   0.05326   0.04593  -0.0534   0.0194   1.0000
  13.250   1.4521   0.05724   0.05007  -0.0533   0.0192   1.0000
  13.500   1.4437   0.06151   0.05450  -0.0535   0.0190   1.0000
  13.750   1.4350   0.06596   0.05911  -0.0539   0.0188   1.0000
  14.000   1.4266   0.07050   0.06379  -0.0545   0.0187   1.0000
  14.250   1.4189   0.07501   0.06842  -0.0552   0.0186   1.0000
  14.500   1.4119   0.07946   0.07299  -0.0559   0.0186   1.0000
  14.750   1.4060   0.08374   0.07739  -0.0565   0.0186   1.0000
  15.000   1.4011   0.08787   0.08162  -0.0571   0.0186   1.0000
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