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GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 281 (DAIMLER XII) AIRFOIL (goe281-il)
Reynolds number: 500,000
Max Cl/Cd: 95.33 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe281-il-500000-n5.txt
Download as CSV file: xf-goe281-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 281 (DAIMLER XII) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3297   0.09592   0.09375  -0.0265   1.0000   0.0075
  -8.250  -0.3283   0.09287   0.09073  -0.0272   1.0000   0.0075
  -8.000  -0.3244   0.08951   0.08740  -0.0289   0.9974   0.0076
  -7.750  -0.3121   0.08515   0.08304  -0.0336   0.9901   0.0078
  -7.500  -0.2973   0.08038   0.07827  -0.0395   0.9824   0.0080
  -7.250  -0.2796   0.07410   0.07198  -0.0480   0.9747   0.0084
  -7.000  -0.2604   0.07024   0.06810  -0.0534   0.9666   0.0089
  -6.750  -0.2407   0.06734   0.06518  -0.0572   0.9583   0.0093
  -6.500  -0.2202   0.06324   0.06103  -0.0624   0.9493   0.0096
  -6.250  -0.1991   0.05872   0.05645  -0.0676   0.9387   0.0100
  -6.000  -0.1756   0.05380   0.05142  -0.0731   0.9279   0.0105
  -5.750  -0.1454   0.04501   0.04240  -0.0817   0.9169   0.0118
  -5.500  -0.1228   0.04365   0.04097  -0.0827   0.9056   0.0122
  -5.250  -0.0983   0.04124   0.03844  -0.0845   0.8926   0.0128
  -4.750  -0.0382   0.02982   0.02627  -0.0904   0.8653   0.0158
  -4.500  -0.0142   0.02924   0.02560  -0.0905   0.8497   0.0163
  -4.250   0.0117   0.02760   0.02375  -0.0910   0.8331   0.0171
  -4.000   0.0393   0.02502   0.02084  -0.0915   0.8163   0.0181
  -3.750   0.0703   0.02088   0.01601  -0.0916   0.8014   0.0209
  -3.500   0.0964   0.01990   0.01489  -0.0919   0.7864   0.0213
  -3.250   0.1232   0.01898   0.01379  -0.0921   0.7718   0.0219
  -3.000   0.1505   0.01804   0.01263  -0.0922   0.7557   0.0227
  -2.750   0.1783   0.01710   0.01143  -0.0922   0.7386   0.0241
  -2.500   0.2065   0.01595   0.00998  -0.0921   0.7215   0.0246
  -2.250   0.2345   0.01507   0.00883  -0.0920   0.7055   0.0251
  -2.000   0.2627   0.01432   0.00785  -0.0920   0.6927   0.0254
  -1.750   0.2909   0.01387   0.00721  -0.0920   0.6807   0.0260
  -1.500   0.3189   0.01355   0.00672  -0.0920   0.6681   0.0264
  -1.250   0.3468   0.01287   0.00587  -0.0920   0.6557   0.0263
  -1.000   0.3747   0.01239   0.00524  -0.0919   0.6435   0.0264
  -0.750   0.4026   0.01206   0.00479  -0.0919   0.6317   0.0266
  -0.500   0.4307   0.01172   0.00436  -0.0919   0.6221   0.0270
  -0.250   0.4584   0.01104   0.00363  -0.0920   0.6132   0.0277
   0.000   0.4861   0.01069   0.00324  -0.0920   0.6015   0.0282
   0.250   0.5138   0.01046   0.00298  -0.0920   0.5884   0.0286
   0.500   0.5415   0.01030   0.00277  -0.0920   0.5730   0.0290
   0.750   0.5692   0.01019   0.00262  -0.0921   0.5566   0.0300
   1.000   0.5969   0.01011   0.00250  -0.0921   0.5391   0.0309
   1.250   0.6242   0.01008   0.00237  -0.0921   0.5114   0.0308
   1.500   0.6506   0.01021   0.00230  -0.0919   0.4709   0.0307
   1.750   0.6772   0.01035   0.00229  -0.0918   0.4430   0.0307
   2.000   0.7042   0.01045   0.00230  -0.0917   0.4259   0.0309
   2.250   0.7315   0.01052   0.00232  -0.0917   0.4141   0.0312
   2.500   0.7590   0.01059   0.00235  -0.0917   0.4048   0.0316
   2.750   0.7862   0.01070   0.00241  -0.0917   0.3944   0.0325
   3.000   0.8136   0.01079   0.00248  -0.0917   0.3836   0.0338
   3.250   0.8408   0.01090   0.00256  -0.0916   0.3733   0.0352
   3.500   0.8679   0.01103   0.00267  -0.0916   0.3603   0.0377
   3.750   0.8948   0.01117   0.00280  -0.0915   0.3456   0.0458
   4.000   0.9171   0.00962   0.00311  -0.0909   0.3299   1.0000
   4.250   0.9429   0.00996   0.00330  -0.0907   0.2982   1.0000
   4.500   0.9668   0.01052   0.00358  -0.0903   0.2515   1.0000
   4.750   0.9914   0.01098   0.00388  -0.0900   0.2235   1.0000
   5.000   1.0164   0.01139   0.00417  -0.0897   0.2033   1.0000
   5.250   1.0414   0.01178   0.00446  -0.0894   0.1806   1.0000
   5.500   1.0642   0.01243   0.00486  -0.0888   0.1372   1.0000
   5.750   1.0872   0.01305   0.00530  -0.0883   0.1094   1.0000
   6.000   1.1094   0.01375   0.00580  -0.0876   0.0776   1.0000
   6.250   1.1272   0.01499   0.00674  -0.0862   0.0177   1.0000
   6.500   1.1513   0.01541   0.00723  -0.0857   0.0140   1.0000
   6.750   1.1754   0.01580   0.00769  -0.0851   0.0125   1.0000
   7.000   1.1989   0.01625   0.00821  -0.0846   0.0112   1.0000
   7.250   1.2217   0.01675   0.00881  -0.0839   0.0102   1.0000
   7.500   1.2433   0.01739   0.00954  -0.0830   0.0093   1.0000
   7.750   1.2632   0.01819   0.01045  -0.0818   0.0085   1.0000
   8.000   1.2849   0.01872   0.01105  -0.0810   0.0078   1.0000
   8.250   1.3051   0.01938   0.01178  -0.0800   0.0072   1.0000
   8.500   1.3242   0.02013   0.01262  -0.0787   0.0068   1.0000
   8.750   1.3422   0.02091   0.01348  -0.0774   0.0064   1.0000
   9.000   1.3582   0.02182   0.01445  -0.0758   0.0061   1.0000
   9.250   1.3691   0.02308   0.01582  -0.0734   0.0058   1.0000
   9.500   1.3788   0.02428   0.01713  -0.0709   0.0056   1.0000
   9.750   1.3877   0.02529   0.01824  -0.0681   0.0055   1.0000
  10.000   1.3956   0.02636   0.01944  -0.0654   0.0052   1.0000
  10.250   1.4029   0.02754   0.02072  -0.0628   0.0050   1.0000
  10.500   1.4103   0.02878   0.02206  -0.0605   0.0047   1.0000
  10.750   1.4159   0.03021   0.02359  -0.0581   0.0045   1.0000
  11.000   1.4200   0.03184   0.02532  -0.0559   0.0044   1.0000
  11.250   1.4236   0.03362   0.02721  -0.0540   0.0042   1.0000
  11.500   1.4264   0.03556   0.02925  -0.0522   0.0041   1.0000
  11.750   1.4283   0.03772   0.03151  -0.0508   0.0041   1.0000
  12.000   1.4288   0.04013   0.03403  -0.0495   0.0040   1.0000
  12.250   1.4277   0.04284   0.03687  -0.0485   0.0039   1.0000
  12.500   1.4242   0.04595   0.04009  -0.0476   0.0038   1.0000
  12.750   1.4172   0.04959   0.04385  -0.0468   0.0037   1.0000
  13.000   1.4143   0.05291   0.04730  -0.0464   0.0037   1.0000
  13.250   1.4113   0.05631   0.05084  -0.0461   0.0036   1.0000
  13.500   1.4075   0.05990   0.05459  -0.0460   0.0036   1.0000
  13.750   1.4026   0.06371   0.05854  -0.0460   0.0035   1.0000
  14.000   1.3968   0.06770   0.06269  -0.0461   0.0035   1.0000
  14.250   1.3904   0.07191   0.06706  -0.0465   0.0034   1.0000
  14.500   1.3831   0.07640   0.07170  -0.0470   0.0034   1.0000
  14.750   1.3750   0.08110   0.07657  -0.0478   0.0033   1.0000
  15.000   1.3659   0.08613   0.08176  -0.0489   0.0033   1.0000
  15.250   1.3561   0.09149   0.08729  -0.0504   0.0033   1.0000
  15.500   1.3455   0.09716   0.09312  -0.0523   0.0032   1.0000
  15.750   1.3340   0.10314   0.09927  -0.0545   0.0032   1.0000
  16.000   1.3221   0.10943   0.10572  -0.0572   0.0032   1.0000
  16.250   1.3101   0.11594   0.11239  -0.0602   0.0032   1.0000
  16.500   1.2974   0.12279   0.11940  -0.0635   0.0031   1.0000
  16.750   1.2848   0.12982   0.12658  -0.0672   0.0031   1.0000
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