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


Details Polar file
Airfoil: CLARK K AIRFOIL (clarkk-il)
Reynolds number: 200,000
Max Cl/Cd: 75.72 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkk-il-200000.txt
Download as CSV file: xf-clarkk-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK K 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3855   0.11617   0.11219  -0.0337   1.0000   0.0605
 -10.750  -0.3868   0.11253   0.10857  -0.0362   1.0000   0.0631
 -10.500  -0.4237   0.10581   0.10196  -0.0473   1.0000   0.0649
 -10.250  -0.4008   0.10305   0.09917  -0.0425   1.0000   0.0658
 -10.000  -0.3886   0.10084   0.09697  -0.0411   1.0000   0.0667
  -9.750  -0.3812   0.09840   0.09453  -0.0407   1.0000   0.0680
  -9.500  -0.3784   0.09561   0.09178  -0.0411   1.0000   0.0697
  -9.250  -0.3562   0.08435   0.08097  -0.0441   1.0000   0.0756
  -9.000  -0.3429   0.08338   0.08002  -0.0399   1.0000   0.0766
  -8.750  -0.3445   0.08209   0.07877  -0.0368   1.0000   0.0776
  -8.500  -0.3528   0.08061   0.07734  -0.0341   1.0000   0.0787
  -8.250  -0.4926   0.07921   0.07583  -0.0406   1.0000   0.0762
  -8.000  -0.4923   0.07848   0.07514  -0.0365   1.0000   0.0770
  -7.750  -0.4994   0.07709   0.07378  -0.0337   1.0000   0.0778
  -7.500  -0.4962   0.06263   0.05883  -0.0559   0.9894   0.0872
  -7.250  -0.4673   0.06133   0.05766  -0.0556   0.9868   0.0885
  -7.000  -0.4415   0.05707   0.05303  -0.0630   0.9805   0.0983
  -6.750  -0.4199   0.05352   0.04958  -0.0645   0.9757   0.1013
  -6.500  -0.3879   0.05244   0.04853  -0.0660   0.9724   0.1054
  -6.250  -0.3632   0.04866   0.04456  -0.0703   0.9665   0.1159
  -5.750  -0.3032   0.04384   0.03941  -0.0770   0.9568   0.1419
  -5.500  -0.2745   0.04299   0.03864  -0.0774   0.9515   0.1485
  -5.250  -0.2458   0.04113   0.03672  -0.0792   0.9458   0.1613
  -5.000  -0.2109   0.03920   0.03470  -0.0822   0.9427   0.1762
  -4.750  -0.1732   0.03732   0.03275  -0.0854   0.9407   0.1926
  -4.250  -0.1101   0.02218   0.01481  -0.0884   0.9273   0.0943
  -4.000  -0.0704   0.02076   0.01309  -0.0904   0.9250   0.0910
  -3.750  -0.0451   0.02001   0.01217  -0.0896   0.9163   0.0903
  -3.500  -0.0091   0.01916   0.01117  -0.0908   0.9121   0.0890
  -3.250   0.0283   0.01846   0.01035  -0.0922   0.9089   0.0880
  -3.000   0.0532   0.01799   0.00983  -0.0913   0.8998   0.0876
  -2.750   0.0866   0.01731   0.00911  -0.0920   0.8950   0.0874
  -2.500   0.1157   0.01669   0.00850  -0.0920   0.8885   0.0876
  -2.250   0.1434   0.01602   0.00788  -0.0917   0.8810   0.0887
  -2.000   0.1750   0.01538   0.00727  -0.0921   0.8763   0.0900
  -1.750   0.1990   0.01504   0.00697  -0.0911   0.8665   0.0905
  -1.500   0.2290   0.01457   0.00650  -0.0911   0.8606   0.0912
  -1.250   0.2538   0.01431   0.00625  -0.0903   0.8510   0.0921
  -1.000   0.2832   0.01396   0.00587  -0.0902   0.8444   0.0934
  -0.750   0.3086   0.01378   0.00568  -0.0894   0.8346   0.0949
  -0.500   0.3380   0.01351   0.00536  -0.0893   0.8276   0.0970
  -0.250   0.3633   0.01337   0.00522  -0.0885   0.8170   0.1007
   0.000   0.3918   0.01312   0.00498  -0.0882   0.8090   0.1075
   0.250   0.4169   0.01274   0.00491  -0.0876   0.7984   0.1781
   0.500   0.4430   0.01247   0.00486  -0.0870   0.7884   0.2535
   0.750   0.4691   0.01198   0.00475  -0.0865   0.7788   0.3762
   1.000   0.4881   0.01118   0.00480  -0.0846   0.7663   0.6249
   1.250   0.5245   0.01049   0.00488  -0.0848   0.7543   0.9340
   1.500   0.5814   0.01040   0.00470  -0.0905   0.7421   1.0000
   1.750   0.6063   0.01046   0.00466  -0.0897   0.7304   1.0000
   2.000   0.6304   0.01054   0.00467  -0.0887   0.7177   1.0000
   2.250   0.6550   0.01063   0.00467  -0.0878   0.7055   1.0000
   2.500   0.6802   0.01072   0.00467  -0.0870   0.6935   1.0000
   2.750   0.7051   0.01081   0.00468  -0.0862   0.6808   1.0000
   3.000   0.7292   0.01092   0.00475  -0.0853   0.6671   1.0000
   3.250   0.7536   0.01104   0.00482  -0.0844   0.6531   1.0000
   3.500   0.7781   0.01117   0.00489  -0.0836   0.6389   1.0000
   3.750   0.8027   0.01131   0.00497  -0.0827   0.6246   1.0000
   4.000   0.8270   0.01145   0.00506  -0.0819   0.6095   1.0000
   4.250   0.8511   0.01162   0.00518  -0.0810   0.5934   1.0000
   4.500   0.8750   0.01180   0.00531  -0.0800   0.5766   1.0000
   4.750   0.8988   0.01201   0.00546  -0.0791   0.5595   1.0000
   5.000   0.9221   0.01223   0.00564  -0.0781   0.5412   1.0000
   5.250   0.9451   0.01249   0.00583  -0.0771   0.5219   1.0000
   5.500   0.9677   0.01278   0.00604  -0.0760   0.5023   1.0000
   5.750   0.9900   0.01309   0.00631  -0.0748   0.4813   1.0000
   6.000   1.0115   0.01342   0.00659  -0.0736   0.4588   1.0000
   6.250   1.0322   0.01382   0.00687  -0.0723   0.4353   1.0000
   6.500   1.0524   0.01422   0.00721  -0.0709   0.4099   1.0000
   6.750   1.0719   0.01469   0.00756  -0.0694   0.3858   1.0000
   7.000   1.0914   0.01516   0.00795  -0.0679   0.3623   1.0000
   7.250   1.1102   0.01569   0.00837  -0.0665   0.3414   1.0000
   7.500   1.1294   0.01619   0.00881  -0.0651   0.3210   1.0000
   7.750   1.1482   0.01669   0.00927  -0.0636   0.3015   1.0000
   8.000   1.1667   0.01722   0.00975  -0.0622   0.2840   1.0000
   8.250   1.1853   0.01774   0.01026  -0.0608   0.2686   1.0000
   8.500   1.2036   0.01827   0.01078  -0.0593   0.2538   1.0000
   8.750   1.2211   0.01881   0.01132  -0.0578   0.2388   1.0000
   9.000   1.2374   0.01937   0.01189  -0.0561   0.2221   1.0000
   9.250   1.2504   0.02001   0.01249  -0.0538   0.2021   1.0000
   9.500   1.2604   0.02083   0.01321  -0.0513   0.1701   1.0000
   9.750   1.2577   0.02262   0.01451  -0.0474   0.1001   1.0000
  10.000   1.2543   0.02467   0.01626  -0.0436   0.0710   1.0000
  10.250   1.2579   0.02625   0.01782  -0.0408   0.0618   1.0000
  10.500   1.2616   0.02786   0.01945  -0.0383   0.0567   1.0000
  10.750   1.2674   0.02936   0.02103  -0.0361   0.0530   1.0000
  11.000   1.2676   0.03133   0.02302  -0.0338   0.0505   1.0000
  11.250   1.2715   0.03312   0.02490  -0.0318   0.0486   1.0000
  11.500   1.2768   0.03486   0.02673  -0.0302   0.0467   1.0000
  11.750   1.2811   0.03675   0.02867  -0.0286   0.0449   1.0000
  12.000   1.2832   0.03887   0.03081  -0.0271   0.0434   1.0000
  12.250   1.2846   0.04118   0.03311  -0.0253   0.0421   1.0000
  12.500   1.2919   0.04297   0.03503  -0.0241   0.0409   1.0000
  12.750   1.2989   0.04484   0.03699  -0.0229   0.0399   1.0000
  13.000   1.3064   0.04671   0.03894  -0.0217   0.0389   1.0000
  13.250   1.3143   0.04857   0.04084  -0.0206   0.0379   1.0000
  13.500   1.3236   0.05036   0.04263  -0.0194   0.0369   1.0000
  13.750   1.3410   0.05200   0.04420  -0.0178   0.0356   1.0000
  14.000   1.3452   0.05419   0.04659  -0.0169   0.0350   1.0000
  14.250   1.3502   0.05645   0.04903  -0.0160   0.0343   1.0000
  14.500   1.3562   0.05876   0.05149  -0.0151   0.0336   1.0000
  14.750   1.3613   0.06121   0.05410  -0.0143   0.0331   1.0000
  15.000   1.3653   0.06382   0.05686  -0.0136   0.0326   1.0000
  15.250   1.3681   0.06658   0.05978  -0.0130   0.0322   1.0000
  15.500   1.3699   0.06947   0.06283  -0.0125   0.0318   1.0000
  15.750   1.3688   0.07266   0.06617  -0.0122   0.0315   1.0000
  16.000   1.3667   0.07602   0.06967  -0.0121   0.0311   1.0000
  16.250   1.3662   0.07935   0.07310  -0.0120   0.0307   1.0000
  16.500   1.3661   0.08311   0.07698  -0.0118   0.0302   1.0000
  16.750   1.3567   0.08809   0.08216  -0.0122   0.0300   1.0000
  17.000   1.3387   0.09339   0.08768  -0.0139   0.0299   1.0000
  17.250   1.3210   0.09902   0.09353  -0.0160   0.0299   1.0000
  17.500   1.3028   0.10508   0.09981  -0.0187   0.0299   1.0000
  17.750   1.2840   0.11162   0.10657  -0.0219   0.0299   1.0000
  18.000   1.2659   0.11841   0.11356  -0.0254   0.0300   1.0000
  18.250   1.2458   0.12583   0.12119  -0.0303   0.0301   1.0000
  18.500   1.2119   0.13697   0.13267  -0.0389   0.0306   1.0000
  18.750   1.0669   0.18250   0.17886  -0.0707   0.0359   1.0000
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