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CLARK W AIRFOIL (clarkw-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: CLARK W AIRFOIL (clarkw-il)
Reynolds number: 200,000
Max Cl/Cd: 73.54 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkw-il-200000.txt
Download as CSV file: xf-clarkw-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK W 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4029   0.08899   0.08552  -0.0330   1.0000   0.0809
  -8.000  -0.4222   0.08756   0.08417  -0.0299   1.0000   0.0820
  -7.750  -0.4484   0.08639   0.08309  -0.0262   1.0000   0.0826
  -7.500  -0.4725   0.08451   0.08128  -0.0244   1.0000   0.0837
  -7.250  -0.4663   0.07266   0.06929  -0.0442   0.9916   0.0885
  -7.000  -0.4441   0.07027   0.06690  -0.0446   0.9880   0.0896
  -6.750  -0.4590   0.04211   0.03741  -0.0641   0.9761   0.0657
  -6.500  -0.4330   0.03730   0.03227  -0.0664   0.9724   0.0617
  -6.250  -0.4100   0.03233   0.02670  -0.0681   0.9680   0.0602
  -6.000  -0.3873   0.02824   0.02192  -0.0685   0.9624   0.0587
  -5.750  -0.3549   0.02564   0.01879  -0.0700   0.9591   0.0584
  -5.500  -0.3180   0.02392   0.01675  -0.0721   0.9569   0.0588
  -5.250  -0.2919   0.02282   0.01545  -0.0719   0.9507   0.0596
  -5.000  -0.2582   0.02186   0.01431  -0.0732   0.9464   0.0614
  -4.750  -0.2203   0.02087   0.01313  -0.0751   0.9437   0.0629
  -4.500  -0.1801   0.01997   0.01207  -0.0775   0.9416   0.0641
  -4.250  -0.1564   0.01906   0.01114  -0.0767   0.9342   0.0657
  -4.000  -0.1201   0.01832   0.01044  -0.0784   0.9304   0.0684
  -3.750  -0.0798   0.01770   0.00980  -0.0808   0.9278   0.0726
  -3.500  -0.0366   0.01694   0.00909  -0.0838   0.9259   0.0795
  -3.250  -0.0120   0.01651   0.00865  -0.0829   0.9166   0.0879
  -3.000   0.0275   0.01552   0.00789  -0.0850   0.9129   0.1231
  -2.750   0.0680   0.01487   0.00741  -0.0873   0.9102   0.1679
  -2.500   0.0911   0.01465   0.00728  -0.0862   0.9006   0.1956
  -2.250   0.1270   0.01423   0.00699  -0.0875   0.8965   0.2323
  -2.000   0.1559   0.01400   0.00685  -0.0875   0.8896   0.2680
  -1.750   0.1860   0.01375   0.00668  -0.0876   0.8828   0.3034
  -1.500   0.2208   0.01345   0.00641  -0.0885   0.8786   0.3400
  -1.250   0.2445   0.01332   0.00636  -0.0874   0.8688   0.3677
  -1.000   0.2766   0.01295   0.00604  -0.0878   0.8634   0.3957
  -0.750   0.3016   0.01275   0.00590  -0.0869   0.8539   0.4208
  -0.500   0.3316   0.01231   0.00558  -0.0869   0.8475   0.4507
  -0.250   0.3552   0.01196   0.00543  -0.0858   0.8375   0.4902
   0.000   0.4029   0.01067   0.00548  -0.0883   0.8322   0.9355
   0.250   0.4919   0.01051   0.00519  -0.1006   0.8257   1.0000
   0.500   0.5180   0.01044   0.00501  -0.0998   0.8152   1.0000
   0.750   0.5417   0.01044   0.00493  -0.0987   0.8028   1.0000
   1.000   0.5664   0.01042   0.00483  -0.0978   0.7909   1.0000
   1.250   0.5919   0.01040   0.00471  -0.0969   0.7790   1.0000
   1.500   0.6167   0.01039   0.00462  -0.0959   0.7660   1.0000
   1.750   0.6402   0.01042   0.00459  -0.0948   0.7514   1.0000
   2.000   0.6639   0.01046   0.00455  -0.0936   0.7363   1.0000
   2.250   0.6876   0.01050   0.00453  -0.0925   0.7205   1.0000
   2.500   0.7113   0.01056   0.00451  -0.0914   0.7036   1.0000
   2.750   0.7347   0.01065   0.00451  -0.0902   0.6860   1.0000
   3.000   0.7576   0.01076   0.00454  -0.0889   0.6670   1.0000
   3.250   0.7797   0.01090   0.00461  -0.0876   0.6459   1.0000
   3.500   0.8019   0.01107   0.00467  -0.0862   0.6246   1.0000
   3.750   0.8240   0.01129   0.00476  -0.0848   0.6040   1.0000
   4.000   0.8451   0.01152   0.00492  -0.0833   0.5818   1.0000
   4.250   0.8663   0.01178   0.00508  -0.0819   0.5607   1.0000
   4.500   0.8876   0.01208   0.00526  -0.0804   0.5411   1.0000
   4.750   0.9088   0.01240   0.00548  -0.0790   0.5222   1.0000
   5.000   0.9296   0.01271   0.00572  -0.0776   0.5028   1.0000
   5.250   0.9506   0.01304   0.00598  -0.0762   0.4846   1.0000
   5.500   0.9717   0.01338   0.00625  -0.0749   0.4679   1.0000
   5.750   0.9929   0.01373   0.00655  -0.0736   0.4521   1.0000
   6.000   1.0146   0.01410   0.00686  -0.0724   0.4381   1.0000
   6.250   1.0367   0.01449   0.00719  -0.0713   0.4255   1.0000
   6.500   1.0576   0.01485   0.00752  -0.0700   0.4108   1.0000
   6.750   1.0773   0.01519   0.00782  -0.0685   0.3941   1.0000
   7.000   1.0968   0.01552   0.00813  -0.0670   0.3777   1.0000
   7.250   1.1169   0.01585   0.00848  -0.0656   0.3634   1.0000
   7.500   1.1371   0.01618   0.00885  -0.0642   0.3494   1.0000
   7.750   1.1568   0.01653   0.00923  -0.0628   0.3352   1.0000
   8.000   1.1758   0.01690   0.00961  -0.0613   0.3203   1.0000
   8.250   1.1940   0.01728   0.01001  -0.0597   0.3044   1.0000
   8.500   1.2110   0.01770   0.01045  -0.0579   0.2867   1.0000
   8.750   1.2263   0.01819   0.01091  -0.0558   0.2668   1.0000
   9.000   1.2407   0.01871   0.01142  -0.0537   0.2415   1.0000
   9.250   1.2501   0.01943   0.01202  -0.0508   0.2104   1.0000
   9.500   1.2556   0.02047   0.01286  -0.0475   0.1704   1.0000
   9.750   1.2568   0.02193   0.01404  -0.0439   0.1350   1.0000
  10.000   1.2581   0.02349   0.01543  -0.0405   0.1115   1.0000
  10.250   1.2597   0.02510   0.01693  -0.0373   0.0966   1.0000
  10.500   1.2654   0.02649   0.01832  -0.0348   0.0861   1.0000
  10.750   1.2711   0.02793   0.01978  -0.0324   0.0787   1.0000
  11.000   1.2745   0.02956   0.02139  -0.0300   0.0733   1.0000
  11.250   1.2814   0.03104   0.02295  -0.0280   0.0688   1.0000
  11.500   1.2876   0.03258   0.02453  -0.0262   0.0650   1.0000
  11.750   1.2886   0.03465   0.02656  -0.0240   0.0618   1.0000
  12.000   1.2971   0.03615   0.02819  -0.0226   0.0589   1.0000
  12.250   1.3033   0.03784   0.02995  -0.0211   0.0562   1.0000
  12.500   1.3077   0.03979   0.03189  -0.0195   0.0540   1.0000
  12.750   1.3140   0.04173   0.03387  -0.0179   0.0519   1.0000
  13.000   1.3209   0.04351   0.03580  -0.0167   0.0498   1.0000
  13.250   1.3274   0.04536   0.03772  -0.0156   0.0479   1.0000
  13.500   1.3342   0.04724   0.03959  -0.0145   0.0461   1.0000
  13.750   1.3458   0.04915   0.04149  -0.0130   0.0444   1.0000
  14.000   1.3507   0.05125   0.04380  -0.0120   0.0433   1.0000
  14.250   1.3559   0.05341   0.04611  -0.0110   0.0419   1.0000
  14.500   1.3600   0.05565   0.04848  -0.0102   0.0407   1.0000
  14.750   1.3646   0.05786   0.05076  -0.0095   0.0395   1.0000
  15.000   1.3758   0.05977   0.05262  -0.0086   0.0381   1.0000
  15.250   1.3800   0.06264   0.05565  -0.0076   0.0372   1.0000
  15.500   1.3752   0.06588   0.05915  -0.0072   0.0367   1.0000
  15.750   1.3695   0.06938   0.06289  -0.0070   0.0362   1.0000
  16.000   1.3628   0.07316   0.06690  -0.0071   0.0357   1.0000
  16.250   1.3546   0.07721   0.07116  -0.0074   0.0352   1.0000
  16.500   1.3454   0.08151   0.07567  -0.0081   0.0347   1.0000
  16.750   1.3357   0.08603   0.08037  -0.0092   0.0343   1.0000
  17.000   1.3261   0.09068   0.08520  -0.0105   0.0338   1.0000
  17.250   1.3169   0.09536   0.09003  -0.0121   0.0334   1.0000
  17.500   1.3047   0.10068   0.09552  -0.0142   0.0331   1.0000
  17.750   1.2915   0.10637   0.10137  -0.0168   0.0328   1.0000
  18.000   1.2755   0.11281   0.10800  -0.0200   0.0326   1.0000
  18.250   1.2510   0.12121   0.11664  -0.0249   0.0327   1.0000
  18.500   1.0064   0.19640   0.19267  -0.0710   0.0446   1.0000
  18.750   1.0757   0.17377   0.17008  -0.0600   0.0373   1.0000
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