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CLARK W AIRFOIL (clarkw-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: CLARK W AIRFOIL (clarkw-il)
Reynolds number: 200,000
Max Cl/Cd: 69.72 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarkw-il-200000-n5.txt
Download as CSV file: xf-clarkw-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4315   0.08999   0.08608  -0.0467   1.0000   0.0329
 -10.000  -0.4457   0.08473   0.08087  -0.0481   1.0000   0.0330
  -9.750  -0.4699   0.07865   0.07487  -0.0494   1.0000   0.0330
  -9.250  -0.6085   0.03918   0.03423  -0.0776   0.9833   0.0328
  -9.000  -0.5964   0.03507   0.02948  -0.0792   0.9763   0.0333
  -8.750  -0.5741   0.03197   0.02599  -0.0809   0.9728   0.0337
  -8.500  -0.5537   0.02990   0.02369  -0.0811   0.9673   0.0340
  -8.250  -0.5279   0.02815   0.02172  -0.0820   0.9633   0.0345
  -8.000  -0.4986   0.02658   0.01993  -0.0834   0.9606   0.0349
  -7.750  -0.4726   0.02535   0.01852  -0.0838   0.9563   0.0356
  -7.500  -0.4463   0.02422   0.01721  -0.0841   0.9514   0.0363
  -7.250  -0.4163   0.02306   0.01584  -0.0851   0.9482   0.0371
  -7.000  -0.3851   0.02192   0.01450  -0.0862   0.9457   0.0377
  -6.750  -0.3607   0.02101   0.01343  -0.0857   0.9397   0.0381
  -6.500  -0.3325   0.02013   0.01240  -0.0860   0.9351   0.0386
  -6.000  -0.2706   0.01858   0.01059  -0.0875   0.9287   0.0397
  -5.750  -0.2473   0.01788   0.00986  -0.0866   0.9216   0.0403
  -5.500  -0.2183   0.01718   0.00914  -0.0870   0.9173   0.0413
  -5.250  -0.1870   0.01661   0.00854  -0.0878   0.9141   0.0426
  -5.000  -0.1626   0.01618   0.00807  -0.0871   0.9071   0.0438
  -4.750  -0.1339   0.01571   0.00754  -0.0872   0.9020   0.0450
  -4.500  -0.1030   0.01525   0.00701  -0.0877   0.8982   0.0462
  -4.250  -0.0780   0.01490   0.00661  -0.0871   0.8910   0.0475
  -4.000  -0.0494   0.01448   0.00618  -0.0871   0.8855   0.0496
  -3.750  -0.0194   0.01411   0.00578  -0.0874   0.8809   0.0528
  -3.500   0.0061   0.01381   0.00550  -0.0869   0.8729   0.0576
  -3.250   0.0360   0.01341   0.00514  -0.0871   0.8667   0.0712
  -3.000   0.0617   0.01310   0.00490  -0.0865   0.8565   0.0920
  -2.750   0.0908   0.01279   0.00461  -0.0865   0.8486   0.1124
  -2.500   0.1172   0.01258   0.00442  -0.0861   0.8390   0.1297
  -2.250   0.1452   0.01233   0.00423  -0.0860   0.8315   0.1521
  -2.000   0.1719   0.01214   0.00409  -0.0856   0.8224   0.1749
  -1.750   0.1991   0.01193   0.00398  -0.0853   0.8140   0.2079
  -1.500   0.2260   0.01176   0.00391  -0.0850   0.8049   0.2422
  -1.250   0.2527   0.01164   0.00385  -0.0847   0.7956   0.2741
  -1.000   0.2802   0.01153   0.00378  -0.0844   0.7866   0.3019
  -0.750   0.3066   0.01146   0.00374  -0.0839   0.7762   0.3261
  -0.500   0.3338   0.01138   0.00367  -0.0836   0.7667   0.3468
  -0.250   0.3602   0.01131   0.00361  -0.0831   0.7558   0.3652
   0.000   0.3865   0.01123   0.00356  -0.0827   0.7448   0.3847
   0.250   0.4129   0.01114   0.00349  -0.0822   0.7336   0.4069
   0.500   0.4384   0.01100   0.00343  -0.0816   0.7215   0.4387
   0.750   0.4616   0.01067   0.00339  -0.0805   0.7086   0.5115
   1.250   0.5506   0.00996   0.00366  -0.0861   0.6794   0.9779
   1.500   0.5951   0.01005   0.00364  -0.0896   0.6621   0.9950
   1.750   0.6279   0.01015   0.00363  -0.0906   0.6445   1.0000
   2.000   0.6510   0.01028   0.00365  -0.0895   0.6268   1.0000
   2.250   0.6738   0.01043   0.00369  -0.0883   0.6084   1.0000
   2.500   0.6962   0.01060   0.00376  -0.0871   0.5893   1.0000
   2.750   0.7184   0.01078   0.00384  -0.0859   0.5696   1.0000
   3.000   0.7402   0.01098   0.00394  -0.0846   0.5503   1.0000
   3.250   0.7617   0.01121   0.00406  -0.0833   0.5309   1.0000
   3.500   0.7829   0.01145   0.00420  -0.0819   0.5120   1.0000
   3.750   0.8040   0.01170   0.00435  -0.0805   0.4944   1.0000
   4.000   0.8254   0.01196   0.00454  -0.0791   0.4785   1.0000
   4.250   0.8468   0.01222   0.00473  -0.0778   0.4632   1.0000
   4.500   0.8683   0.01249   0.00494  -0.0766   0.4487   1.0000
   4.750   0.8899   0.01277   0.00518  -0.0753   0.4347   1.0000
   5.000   0.9113   0.01307   0.00542  -0.0741   0.4204   1.0000
   5.250   0.9325   0.01338   0.00567  -0.0728   0.4059   1.0000
   5.500   0.9538   0.01369   0.00594  -0.0716   0.3924   1.0000
   5.750   0.9751   0.01402   0.00622  -0.0704   0.3799   1.0000
   6.000   0.9968   0.01432   0.00651  -0.0693   0.3667   1.0000
   6.250   1.0187   0.01463   0.00681  -0.0682   0.3552   1.0000
   6.500   1.0402   0.01495   0.00714  -0.0671   0.3445   1.0000
   6.750   1.0605   0.01531   0.00746  -0.0658   0.3289   1.0000
   7.000   1.0800   0.01569   0.00780  -0.0643   0.3099   1.0000
   7.250   1.0994   0.01610   0.00817  -0.0629   0.2920   1.0000
   7.500   1.1193   0.01649   0.00855  -0.0616   0.2773   1.0000
   7.750   1.1387   0.01691   0.00895  -0.0603   0.2621   1.0000
   8.000   1.1575   0.01735   0.00938  -0.0588   0.2461   1.0000
   8.250   1.1751   0.01786   0.00986  -0.0572   0.2276   1.0000
   8.500   1.1906   0.01845   0.01038  -0.0553   0.2065   1.0000
   8.750   1.2043   0.01911   0.01095  -0.0532   0.1815   1.0000
   9.000   1.2159   0.01991   0.01164  -0.0508   0.1552   1.0000
   9.250   1.2265   0.02083   0.01244  -0.0484   0.1332   1.0000
   9.500   1.2375   0.02176   0.01330  -0.0461   0.1163   1.0000
   9.750   1.2485   0.02271   0.01421  -0.0439   0.1024   1.0000
  10.000   1.2594   0.02368   0.01516  -0.0418   0.0902   1.0000
  10.250   1.2699   0.02470   0.01617  -0.0398   0.0795   1.0000
  10.500   1.2793   0.02580   0.01727  -0.0377   0.0707   1.0000
  10.750   1.2894   0.02688   0.01838  -0.0358   0.0640   1.0000
  11.000   1.2978   0.02811   0.01963  -0.0339   0.0591   1.0000
  11.250   1.3065   0.02934   0.02092  -0.0321   0.0549   1.0000
  11.500   1.3123   0.03083   0.02244  -0.0302   0.0516   1.0000
  11.750   1.3206   0.03218   0.02389  -0.0286   0.0489   1.0000
  12.000   1.3273   0.03370   0.02550  -0.0271   0.0463   1.0000
  12.250   1.3312   0.03549   0.02734  -0.0256   0.0441   1.0000
  12.500   1.3351   0.03736   0.02929  -0.0241   0.0423   1.0000
  12.750   1.3406   0.03916   0.03121  -0.0230   0.0404   1.0000
  13.000   1.3443   0.04116   0.03331  -0.0219   0.0387   1.0000
  13.250   1.3456   0.04347   0.03569  -0.0209   0.0372   1.0000
  13.500   1.3442   0.04612   0.03842  -0.0201   0.0360   1.0000
  13.750   1.3469   0.04844   0.04089  -0.0194   0.0347   1.0000
  14.000   1.3481   0.05099   0.04356  -0.0189   0.0335   1.0000
  14.250   1.3483   0.05375   0.04643  -0.0186   0.0323   1.0000
  14.500   1.3469   0.05679   0.04956  -0.0185   0.0313   1.0000
  14.750   1.3427   0.06024   0.05307  -0.0186   0.0304   1.0000
  15.000   1.3410   0.06350   0.05646  -0.0188   0.0296   1.0000
  15.250   1.3399   0.06679   0.05989  -0.0191   0.0286   1.0000
  15.500   1.3376   0.07029   0.06351  -0.0195   0.0278   1.0000
  15.750   1.3346   0.07395   0.06731  -0.0202   0.0270   1.0000
  16.000   1.3311   0.07779   0.07124  -0.0210   0.0263   1.0000
  16.250   1.3268   0.08181   0.07536  -0.0220   0.0257   1.0000
  16.500   1.3212   0.08600   0.07960  -0.0231   0.0252   1.0000
  16.750   1.3175   0.09001   0.08375  -0.0241   0.0246   1.0000
  17.000   1.3138   0.09411   0.08801  -0.0253   0.0239   1.0000
  17.250   1.3094   0.09839   0.09242  -0.0266   0.0232   1.0000
  17.500   1.3047   0.10277   0.09692  -0.0282   0.0227   1.0000
  17.750   1.2997   0.10723   0.10149  -0.0298   0.0221   1.0000
  18.000   1.2948   0.11174   0.10611  -0.0316   0.0217   1.0000
  18.250   1.2899   0.11628   0.11073  -0.0335   0.0213   1.0000
  18.500   1.2853   0.12077   0.11529  -0.0354   0.0209   1.0000
  18.750   1.2811   0.12516   0.11977  -0.0373   0.0206   1.0000
  19.000   1.2748   0.13018   0.12496  -0.0397   0.0202   1.0000
  19.250   1.2679   0.13541   0.13036  -0.0423   0.0198   1.0000
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