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GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 281 (DAIMLER XII) AIRFOIL (goe281-il)
Reynolds number: 200,000
Max Cl/Cd: 79.06 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe281-il-200000.txt
Download as CSV file: xf-goe281-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3436   0.10423   0.10082  -0.0296   1.0000   0.0263
  -8.250  -0.3465   0.10202   0.09867  -0.0305   1.0000   0.0263
  -8.000  -0.3474   0.09955   0.09626  -0.0320   1.0000   0.0264
  -7.750  -0.3469   0.09686   0.09361  -0.0338   1.0000   0.0264
  -7.500  -0.3467   0.09189   0.08870  -0.0302   1.0000   0.0268
  -7.250  -0.3443   0.08860   0.08544  -0.0270   1.0000   0.0272
  -7.000  -0.3447   0.08604   0.08292  -0.0255   1.0000   0.0276
  -6.750  -0.3462   0.08368   0.08060  -0.0246   1.0000   0.0280
  -6.500  -0.3478   0.08137   0.07833  -0.0240   1.0000   0.0284
  -6.250  -0.3489   0.07906   0.07606  -0.0236   1.0000   0.0289
  -6.000  -0.3488   0.07672   0.07374  -0.0236   1.0000   0.0297
  -5.750  -0.3382   0.07359   0.07061  -0.0264   0.9989   0.0311
  -5.500  -0.2660   0.06734   0.06402  -0.0469   0.9929   0.0339
  -5.250  -0.2330   0.06038   0.05695  -0.0540   0.9878   0.0346
  -5.000  -0.2078   0.05616   0.05276  -0.0567   0.9842   0.0359
  -4.750  -0.1737   0.05232   0.04885  -0.0616   0.9785   0.0379
  -4.500  -0.1069   0.04921   0.04506  -0.0722   0.9731   0.0441
  -4.250  -0.0793   0.04261   0.03856  -0.0766   0.9703   0.0462
  -4.000  -0.0478   0.03980   0.03569  -0.0795   0.9633   0.0493
  -3.750   0.0038   0.03629   0.03155  -0.0854   0.9591   0.0576
  -3.500   0.0404   0.03304   0.02841  -0.0895   0.9565   0.0620
  -3.250   0.0792   0.03050   0.02548  -0.0925   0.9489   0.0727
  -1.500   0.2944   0.01929   0.01363  -0.1005   0.8864   0.2488
  -1.250   0.3196   0.01817   0.01255  -0.0998   0.8740   0.2864
  -1.000   0.3508   0.01700   0.01112  -0.0996   0.8618   0.2873
  -0.750   0.3996   0.01552   0.00815  -0.0973   0.8520   0.0815
  -0.500   0.4279   0.01461   0.00703  -0.0965   0.8405   0.0735
  -0.250   0.4555   0.01439   0.00665  -0.0957   0.8271   0.0695
   0.000   0.4821   0.01362   0.00584  -0.0950   0.8129   0.0674
   0.250   0.5087   0.01312   0.00530  -0.0942   0.7981   0.0659
   0.500   0.5353   0.01274   0.00487  -0.0936   0.7831   0.0652
   0.750   0.5620   0.01245   0.00454  -0.0930   0.7674   0.0654
   1.000   0.5887   0.01224   0.00428  -0.0925   0.7511   0.0664
   1.250   0.6155   0.01215   0.00410  -0.0921   0.7349   0.0699
   1.500   0.6426   0.01203   0.00390  -0.0917   0.7193   0.0737
   1.750   0.6696   0.01200   0.00380  -0.0913   0.7039   0.0786
   2.000   0.6965   0.01182   0.00378  -0.0909   0.6884   0.1688
   2.250   0.7203   0.01018   0.00383  -0.0899   0.6732   1.0000
   2.500   0.7469   0.01037   0.00385  -0.0894   0.6564   1.0000
   2.750   0.7731   0.01057   0.00389  -0.0889   0.6381   1.0000
   3.000   0.7992   0.01076   0.00397  -0.0885   0.6170   1.0000
   3.250   0.8252   0.01097   0.00405  -0.0880   0.5963   1.0000
   3.500   0.8512   0.01117   0.00418  -0.0876   0.5752   1.0000
   3.750   0.8770   0.01136   0.00429  -0.0871   0.5532   1.0000
   4.000   0.9027   0.01155   0.00441  -0.0867   0.5304   1.0000
   4.250   0.9282   0.01179   0.00455  -0.0862   0.5081   1.0000
   4.500   0.9535   0.01206   0.00476  -0.0858   0.4864   1.0000
   4.750   0.9784   0.01240   0.00499  -0.0852   0.4659   1.0000
   5.000   1.0031   0.01278   0.00528  -0.0847   0.4469   1.0000
   5.250   1.0274   0.01319   0.00561  -0.0842   0.4249   1.0000
   5.500   1.0509   0.01362   0.00597  -0.0835   0.3982   1.0000
   5.750   1.0745   0.01402   0.00630  -0.0829   0.3719   1.0000
   6.000   1.0983   0.01439   0.00664  -0.0823   0.3472   1.0000
   6.250   1.1213   0.01478   0.00695  -0.0816   0.3123   1.0000
   6.500   1.1427   0.01536   0.00737  -0.0808   0.2755   1.0000
   6.750   1.1639   0.01601   0.00787  -0.0799   0.2448   1.0000
   7.000   1.1848   0.01670   0.00843  -0.0790   0.2158   1.0000
   7.250   1.2053   0.01743   0.00901  -0.0781   0.1796   1.0000
   7.500   1.2235   0.01842   0.00967  -0.0768   0.1308   1.0000
   7.750   1.2404   0.01956   0.01056  -0.0754   0.0903   1.0000
   8.000   1.2501   0.02146   0.01201  -0.0729   0.0345   1.0000
   8.250   1.2685   0.02237   0.01305  -0.0714   0.0310   1.0000
   8.500   1.2853   0.02339   0.01424  -0.0698   0.0287   1.0000
   8.750   1.2991   0.02465   0.01566  -0.0678   0.0264   1.0000
   9.000   1.3101   0.02602   0.01723  -0.0654   0.0252   1.0000
   9.250   1.3164   0.02760   0.01902  -0.0624   0.0246   1.0000
   9.500   1.3207   0.02902   0.02056  -0.0591   0.0244   1.0000
   9.750   1.3243   0.03055   0.02221  -0.0559   0.0242   1.0000
  10.000   1.3274   0.03225   0.02402  -0.0530   0.0240   1.0000
  10.250   1.3307   0.03410   0.02596  -0.0503   0.0239   1.0000
  10.500   1.3352   0.03604   0.02799  -0.0479   0.0238   1.0000
  10.750   1.3416   0.03800   0.03004  -0.0458   0.0236   1.0000
  11.000   1.3495   0.03991   0.03205  -0.0439   0.0232   1.0000
  11.250   1.3580   0.04186   0.03415  -0.0422   0.0226   1.0000
  11.500   1.3685   0.04393   0.03633  -0.0405   0.0223   1.0000
  11.750   1.3813   0.04619   0.03873  -0.0389   0.0225   1.0000
  12.000   1.3939   0.04874   0.04145  -0.0374   0.0229   1.0000
  12.250   1.4063   0.05177   0.04469  -0.0359   0.0234   1.0000
  12.500   1.4410   0.05608   0.04914  -0.0360   0.0249   1.0000
  12.750   1.4379   0.05736   0.05065  -0.0336   0.0255   1.0000
  13.000   1.4286   0.05955   0.05325  -0.0313   0.0268   1.0000
  13.250   1.4118   0.06403   0.05824  -0.0295   0.0289   1.0000
  13.500   1.4001   0.06914   0.06367  -0.0286   0.0308   1.0000
  13.750   1.4021   0.07310   0.06806  -0.0273   0.0359   1.0000
  14.000   1.3729   0.07925   0.07458  -0.0283   0.0370   1.0000
  14.250   1.3471   0.08581   0.08144  -0.0301   0.0379   1.0000
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