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CLARK YS AIRFOIL (clarkys-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: CLARK YS AIRFOIL (clarkys-il)
Reynolds number: 500,000
Max Cl/Cd: 76.53 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkys-il-500000.txt
Download as CSV file: xf-clarkys-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK YS 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4742   0.08575   0.08322  -0.0110   0.8136   0.0388
 -10.000  -0.5120   0.07274   0.07025  -0.0181   0.8129   0.0393
  -9.250  -0.7427   0.04580   0.04218  -0.0190   0.8124   0.0330
  -9.000  -0.7382   0.04255   0.03874  -0.0165   0.8086   0.0315
  -8.750  -0.7480   0.03797   0.03376  -0.0123   0.8049   0.0313
  -8.500  -0.7508   0.03410   0.02943  -0.0083   0.8014   0.0313
  -8.250  -0.7437   0.03139   0.02634  -0.0053   0.7978   0.0316
  -8.000  -0.7301   0.02981   0.02444  -0.0030   0.7939   0.0320
  -7.750  -0.7219   0.02658   0.02075  -0.0001   0.7903   0.0327
  -7.500  -0.7041   0.02463   0.01861   0.0014   0.7871   0.0333
  -7.250  -0.6828   0.02337   0.01724   0.0024   0.7834   0.0339
  -7.000  -0.6604   0.02225   0.01598   0.0034   0.7795   0.0344
  -6.750  -0.6371   0.02126   0.01487   0.0042   0.7760   0.0349
  -6.500  -0.6134   0.02046   0.01393   0.0051   0.7727   0.0356
  -6.250  -0.5886   0.01966   0.01302   0.0057   0.7689   0.0364
  -6.000  -0.5632   0.01873   0.01197   0.0063   0.7648   0.0369
  -5.750  -0.5374   0.01789   0.01101   0.0069   0.7611   0.0375
  -5.500  -0.5114   0.01717   0.01016   0.0074   0.7578   0.0379
  -5.250  -0.4848   0.01655   0.00946   0.0078   0.7539   0.0384
  -5.000  -0.4583   0.01614   0.00898   0.0082   0.7492   0.0389
  -4.750  -0.4320   0.01489   0.00766   0.0086   0.7448   0.0399
  -4.500  -0.4065   0.01423   0.00695   0.0092   0.7407   0.0407
  -4.250  -0.3805   0.01370   0.00643   0.0097   0.7349   0.0416
  -4.000  -0.3547   0.01325   0.00595   0.0103   0.7300   0.0424
  -3.750  -0.3290   0.01288   0.00552   0.0109   0.7259   0.0435
  -3.500  -0.3028   0.01249   0.00514   0.0114   0.7199   0.0447
  -3.250  -0.2766   0.01217   0.00477   0.0119   0.7143   0.0460
  -3.000  -0.2509   0.01181   0.00435   0.0126   0.7092   0.0477
  -2.750  -0.2248   0.01142   0.00400   0.0131   0.7024   0.0505
  -2.500  -0.1984   0.01115   0.00372   0.0136   0.6970   0.0538
  -2.250  -0.1720   0.01088   0.00345   0.0141   0.6920   0.0597
  -2.000  -0.1461   0.01052   0.00321   0.0146   0.6856   0.0828
  -1.750  -0.1211   0.01011   0.00298   0.0152   0.6800   0.1271
  -1.500  -0.0966   0.00970   0.00284   0.0159   0.6732   0.1950
  -1.250  -0.0725   0.00933   0.00272   0.0167   0.6665   0.2642
  -1.000  -0.0490   0.00901   0.00260   0.0176   0.6601   0.3276
  -0.750  -0.0298   0.00849   0.00248   0.0193   0.6529   0.4339
  -0.500  -0.0314   0.00736   0.00219   0.0254   0.6472   0.6659
  -0.250  -0.0116   0.00718   0.00272   0.0282   0.6396   0.8933
   0.000   0.0260   0.00760   0.00308   0.0269   0.6320   0.9130
   0.250   0.0618   0.00802   0.00347   0.0260   0.6228   0.9261
   0.500   0.1614   0.00930   0.00463   0.0120   0.6108   0.9386
   0.750   0.2530   0.01020   0.00541  -0.0004   0.5983   0.9517
   1.000   0.3237   0.01044   0.00556  -0.0088   0.5852   0.9630
   1.250   0.3602   0.01061   0.00569  -0.0104   0.5727   0.9708
   1.500   0.4194   0.01040   0.00539  -0.0169   0.5569   0.9779
   1.750   0.4462   0.01065   0.00558  -0.0166   0.5430   0.9824
   2.000   0.5094   0.01009   0.00492  -0.0240   0.5233   0.9909
   2.250   0.5684   0.00953   0.00428  -0.0307   0.5004   1.0000
   2.500   0.5932   0.00961   0.00427  -0.0302   0.4786   1.0000
   2.750   0.6179   0.00973   0.00428  -0.0296   0.4547   1.0000
   3.000   0.6426   0.00987   0.00432  -0.0291   0.4304   1.0000
   3.250   0.6671   0.01003   0.00438  -0.0286   0.4090   1.0000
   3.500   0.6918   0.01018   0.00445  -0.0281   0.3913   1.0000
   3.750   0.7165   0.01034   0.00454  -0.0276   0.3771   1.0000
   4.000   0.7410   0.01052   0.00464  -0.0271   0.3636   1.0000
   4.250   0.7658   0.01064   0.00475  -0.0267   0.3535   1.0000
   4.500   0.7566   0.01134   0.00542  -0.0190   0.3485   0.9929
   4.750   0.7780   0.01142   0.00552  -0.0178   0.3417   0.9915
   5.000   0.7987   0.01160   0.00567  -0.0165   0.3345   0.9903
   5.250   0.8213   0.01171   0.00581  -0.0156   0.3279   0.9898
   5.500   0.8430   0.01187   0.00596  -0.0145   0.3207   0.9892
   5.750   0.8635   0.01203   0.00614  -0.0131   0.3146   0.9883
   6.000   0.8841   0.01216   0.00630  -0.0118   0.3079   0.9876
   6.250   0.9042   0.01237   0.00648  -0.0105   0.3006   0.9870
   6.500   0.9252   0.01248   0.00663  -0.0093   0.2912   0.9865
   6.750   0.9458   0.01264   0.00680  -0.0080   0.2817   0.9861
   7.000   0.9664   0.01283   0.00697  -0.0068   0.2709   0.9858
   7.250   0.9877   0.01297   0.00713  -0.0057   0.2588   0.9856
   7.500   1.0086   0.01318   0.00732  -0.0046   0.2437   0.9855
   7.750   1.0292   0.01345   0.00754  -0.0036   0.2251   0.9855
   8.000   1.0490   0.01385   0.00783  -0.0025   0.1983   0.9856
   8.250   1.0676   0.01439   0.00824  -0.0014   0.1715   0.9858
   8.500   1.0859   0.01497   0.00872  -0.0002   0.1493   0.9861
   8.750   1.1042   0.01557   0.00922   0.0009   0.1295   0.9866
   9.000   1.1248   0.01609   0.00969   0.0016   0.1164   0.9873
   9.250   1.1447   0.01658   0.01016   0.0024   0.1066   0.9880
   9.500   1.1628   0.01710   0.01067   0.0036   0.0979   0.9887
   9.750   1.1807   0.01763   0.01119   0.0047   0.0896   0.9895
  10.000   1.1984   0.01813   0.01170   0.0058   0.0816   0.9904
  10.250   1.2144   0.01873   0.01229   0.0072   0.0732   0.9915
  10.500   1.2280   0.01943   0.01294   0.0088   0.0600   0.9928
  10.750   1.2364   0.02075   0.01405   0.0105   0.0338   0.9944
  11.000   1.2467   0.02207   0.01531   0.0114   0.0244   0.9962
  11.250   1.2531   0.02319   0.01648   0.0130   0.0220   0.9985
  11.500   1.2580   0.02450   0.01788   0.0142   0.0207   1.0000
  11.750   1.2476   0.02566   0.01913   0.0185   0.0201   1.0000
  12.000   1.2379   0.02685   0.02039   0.0226   0.0197   1.0000
  12.250   1.2280   0.02804   0.02164   0.0267   0.0193   1.0000
  12.500   1.2151   0.02943   0.02309   0.0310   0.0187   1.0000
  12.750   1.2026   0.03114   0.02485   0.0347   0.0181   1.0000
  13.000   1.1970   0.03282   0.02661   0.0372   0.0180   1.0000
  13.250   1.1853   0.03536   0.02922   0.0393   0.0174   1.0000
  13.500   1.1820   0.03750   0.03144   0.0406   0.0173   1.0000
  13.750   1.1803   0.03966   0.03369   0.0416   0.0169   1.0000
  14.000   1.1765   0.04219   0.03631   0.0423   0.0167   1.0000
  14.250   1.1722   0.04493   0.03914   0.0427   0.0164   1.0000
  14.500   1.1664   0.04798   0.04228   0.0428   0.0161   1.0000
  14.750   1.1616   0.05116   0.04555   0.0426   0.0158   1.0000
  15.000   1.1558   0.05459   0.04907   0.0422   0.0156   1.0000
  15.250   1.1494   0.05823   0.05279   0.0416   0.0154   1.0000
  15.500   1.1435   0.06191   0.05655   0.0408   0.0153   1.0000
  15.750   1.1368   0.06579   0.06052   0.0399   0.0151   1.0000
  16.000   1.1289   0.06990   0.06470   0.0389   0.0148   1.0000
  16.250   1.1224   0.07392   0.06879   0.0378   0.0147   1.0000
  16.500   1.1169   0.07779   0.07273   0.0367   0.0146   1.0000
  16.750   1.1100   0.08180   0.07679   0.0357   0.0144   1.0000
  17.000   1.1035   0.08551   0.08054   0.0351   0.0141   1.0000
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