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CLARK K AIRFOIL (clarkk-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: CLARK K AIRFOIL (clarkk-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.41 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkk-il-1000000.txt
Download as CSV file: xf-clarkk-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4838   0.09626   0.09444  -0.0410   1.0000   0.0273
 -11.250  -0.4726   0.09477   0.09296  -0.0417   1.0000   0.0275
 -11.000  -0.7590   0.03500   0.03221  -0.0830   0.9938   0.0315
 -10.750  -0.7302   0.03483   0.03203  -0.0841   0.9917   0.0317
 -10.500  -0.7003   0.03469   0.03188  -0.0853   0.9895   0.0319
 -10.250  -0.6703   0.03431   0.03148  -0.0868   0.9876   0.0321
 -10.000  -0.6386   0.03410   0.03127  -0.0883   0.9861   0.0324
  -9.750  -0.6062   0.03397   0.03115  -0.0899   0.9849   0.0327
  -9.500  -0.5761   0.03323   0.03035  -0.0916   0.9833   0.0333
  -9.250  -0.5559   0.03112   0.02805  -0.0924   0.9780   0.0342
  -9.000  -0.5453   0.02610   0.02233  -0.0929   0.9713   0.0365
  -8.750  -0.5210   0.02541   0.02162  -0.0930   0.9658   0.0369
  -8.500  -0.4958   0.02505   0.02127  -0.0928   0.9598   0.0372
  -8.250  -0.4699   0.02472   0.02092  -0.0928   0.9545   0.0376
  -8.000  -0.4469   0.02422   0.02039  -0.0923   0.9467   0.0380
  -7.750  -0.4231   0.02355   0.01962  -0.0919   0.9400   0.0386
  -7.500  -0.4004   0.02277   0.01873  -0.0913   0.9315   0.0395
  -7.250  -0.3780   0.02154   0.01728  -0.0906   0.9240   0.0403
  -7.000  -0.3550   0.02044   0.01596  -0.0900   0.9154   0.0409
  -6.750  -0.3317   0.01974   0.01493  -0.0893   0.9076   0.0421
  -6.500  -0.3085   0.01816   0.01328  -0.0890   0.8993   0.0428
  -6.250  -0.2824   0.01771   0.01283  -0.0889   0.8919   0.0433
  -6.000  -0.2563   0.01721   0.01231  -0.0887   0.8836   0.0439
  -5.500  -0.2045   0.01585   0.01075  -0.0881   0.8675   0.0448
  -5.000  -0.1517   0.01470   0.00938  -0.0876   0.8511   0.0459
  -4.750  -0.1252   0.01408   0.00864  -0.0873   0.8431   0.0461
  -4.500  -0.0983   0.01345   0.00793  -0.0871   0.8347   0.0463
  -4.250  -0.0714   0.01292   0.00729  -0.0868   0.8267   0.0465
  -4.000  -0.0441   0.01243   0.00675  -0.0866   0.8181   0.0468
  -3.750  -0.0170   0.01203   0.00627  -0.0864   0.8100   0.0472
  -3.500   0.0106   0.01171   0.00590  -0.0863   0.8015   0.0476
  -3.250   0.0382   0.01173   0.00583  -0.0861   0.7932   0.0481
  -3.000   0.0656   0.01133   0.00538  -0.0859   0.7846   0.0487
  -2.750   0.0923   0.01065   0.00468  -0.0857   0.7765   0.0489
  -2.500   0.1192   0.01014   0.00416  -0.0855   0.7678   0.0492
  -2.250   0.1460   0.00976   0.00377  -0.0853   0.7594   0.0496
  -2.000   0.1730   0.00944   0.00346  -0.0851   0.7504   0.0500
  -1.750   0.2001   0.00920   0.00320  -0.0848   0.7417   0.0504
  -1.500   0.2273   0.00900   0.00298  -0.0846   0.7324   0.0509
  -1.250   0.2546   0.00882   0.00279  -0.0845   0.7233   0.0515
  -0.750   0.3088   0.00857   0.00248  -0.0840   0.6997   0.0531
  -0.500   0.3359   0.00846   0.00234  -0.0838   0.6867   0.0537
  -0.250   0.3631   0.00837   0.00221  -0.0835   0.6761   0.0543
   0.000   0.3905   0.00829   0.00210  -0.0834   0.6653   0.0548
   0.250   0.4180   0.00822   0.00201  -0.0832   0.6541   0.0553
   0.500   0.4453   0.00817   0.00194  -0.0830   0.6429   0.0557
   1.000   0.4997   0.00804   0.00173  -0.0826   0.6187   0.0571
   1.250   0.5268   0.00799   0.00165  -0.0824   0.6052   0.0584
   1.500   0.5540   0.00798   0.00161  -0.0822   0.5922   0.0601
   1.750   0.5811   0.00800   0.00160  -0.0820   0.5791   0.0618
   2.000   0.6080   0.00805   0.00160  -0.0818   0.5648   0.0631
   2.500   0.6620   0.00817   0.00164  -0.0813   0.5358   0.0666
   2.750   0.6890   0.00822   0.00167  -0.0811   0.5223   0.0718
   3.000   0.7150   0.00802   0.00175  -0.0808   0.5085   0.2133
   3.250   0.7378   0.00726   0.00191  -0.0804   0.4941   0.5799
   3.500   0.7581   0.00650   0.00214  -0.0785   0.4797   0.9656
   3.750   0.8086   0.00669   0.00226  -0.0836   0.4605   1.0000
   4.000   0.8329   0.00686   0.00236  -0.0828   0.4447   1.0000
   4.250   0.8569   0.00706   0.00248  -0.0820   0.4258   1.0000
   4.500   0.8801   0.00732   0.00262  -0.0812   0.4007   1.0000
   4.750   0.9037   0.00759   0.00278  -0.0803   0.3761   1.0000
   5.000   0.9272   0.00788   0.00295  -0.0795   0.3515   1.0000
   5.250   0.9506   0.00819   0.00314  -0.0787   0.3271   1.0000
   5.500   0.9742   0.00850   0.00334  -0.0780   0.3052   1.0000
   5.750   0.9976   0.00883   0.00356  -0.0772   0.2819   1.0000
   6.000   1.0207   0.00920   0.00380  -0.0764   0.2588   1.0000
   6.250   1.0445   0.00950   0.00403  -0.0757   0.2417   1.0000
   6.500   1.0686   0.00980   0.00426  -0.0751   0.2278   1.0000
   6.750   1.0923   0.01012   0.00451  -0.0744   0.2130   1.0000
   7.000   1.1159   0.01044   0.00476  -0.0737   0.1996   1.0000
   7.250   1.1396   0.01075   0.00502  -0.0731   0.1865   1.0000
   7.500   1.1627   0.01110   0.00530  -0.0723   0.1709   1.0000
   7.750   1.1849   0.01152   0.00562  -0.0715   0.1513   1.0000
   8.000   1.2030   0.01222   0.00611  -0.0700   0.1169   1.0000
   8.250   1.2141   0.01344   0.00697  -0.0675   0.0636   1.0000
   8.500   1.2279   0.01442   0.00775  -0.0653   0.0359   1.0000
   8.750   1.2471   0.01499   0.00828  -0.0640   0.0305   1.0000
   9.000   1.2676   0.01543   0.00875  -0.0629   0.0282   1.0000
   9.250   1.2861   0.01596   0.00927  -0.0614   0.0262   1.0000
   9.500   1.3031   0.01649   0.00984  -0.0597   0.0247   1.0000
   9.750   1.3213   0.01695   0.01033  -0.0582   0.0237   1.0000
  10.000   1.3383   0.01747   0.01088  -0.0566   0.0227   1.0000
  10.250   1.3533   0.01813   0.01156  -0.0548   0.0216   1.0000
  10.500   1.3667   0.01888   0.01236  -0.0528   0.0206   1.0000
  10.750   1.3835   0.01943   0.01295  -0.0513   0.0201   1.0000
  11.000   1.3989   0.02007   0.01363  -0.0497   0.0194   1.0000
  11.250   1.4136   0.02077   0.01438  -0.0481   0.0188   1.0000
  11.500   1.4268   0.02158   0.01522  -0.0464   0.0182   1.0000
  11.750   1.4362   0.02267   0.01635  -0.0444   0.0176   1.0000
  12.000   1.4425   0.02400   0.01776  -0.0421   0.0171   1.0000
  12.250   1.4560   0.02486   0.01868  -0.0408   0.0168   1.0000
  12.500   1.4682   0.02584   0.01972  -0.0394   0.0164   1.0000
  12.750   1.4795   0.02692   0.02085  -0.0380   0.0159   1.0000
  13.000   1.4901   0.02809   0.02207  -0.0367   0.0155   1.0000
  13.250   1.4996   0.02936   0.02340  -0.0354   0.0152   1.0000
  13.500   1.5073   0.03084   0.02492  -0.0342   0.0148   1.0000
  13.750   1.5112   0.03270   0.02686  -0.0328   0.0145   1.0000
  14.000   1.5082   0.03525   0.02950  -0.0312   0.0141   1.0000
  14.250   1.5070   0.03776   0.03210  -0.0300   0.0139   1.0000
  14.500   1.5132   0.03962   0.03404  -0.0293   0.0138   1.0000
  14.750   1.5175   0.04172   0.03622  -0.0286   0.0136   1.0000
  15.000   1.5202   0.04406   0.03865  -0.0281   0.0134   1.0000
  15.250   1.5219   0.04660   0.04128  -0.0276   0.0132   1.0000
  15.500   1.5226   0.04931   0.04408  -0.0274   0.0130   1.0000
  15.750   1.5221   0.05226   0.04711  -0.0272   0.0128   1.0000
  16.000   1.5212   0.05536   0.05029  -0.0273   0.0126   1.0000
  16.250   1.5191   0.05870   0.05372  -0.0275   0.0124   1.0000
  16.500   1.5161   0.06222   0.05733  -0.0279   0.0123   1.0000
  16.750   1.5124   0.06593   0.06112  -0.0285   0.0121   1.0000
  17.000   1.5072   0.06994   0.06521  -0.0292   0.0120   1.0000
  17.250   1.5004   0.07425   0.06961  -0.0302   0.0119   1.0000
  17.500   1.4919   0.07883   0.07429  -0.0313   0.0117   1.0000
  17.750   1.4805   0.08393   0.07948  -0.0326   0.0116   1.0000
  18.000   1.4671   0.08939   0.08504  -0.0341   0.0114   1.0000
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