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CLARK K AIRFOIL (clarkk-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: CLARK K AIRFOIL (clarkk-il)
Reynolds number: 100,000
Max Cl/Cd: 54.06 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkk-il-100000.txt
Download as CSV file: xf-clarkk-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4074   0.10020   0.09515  -0.0382   1.0000   0.1537
  -8.500  -0.3634   0.09529   0.09014  -0.0345   1.0000   0.1593
  -8.250  -0.3700   0.09354   0.08847  -0.0335   1.0000   0.1655
  -8.000  -0.4176   0.09354   0.08870  -0.0317   1.0000   0.1682
  -7.750  -0.4720   0.09286   0.08817  -0.0324   1.0000   0.1691
  -7.500  -0.4020   0.08791   0.08312  -0.0263   1.0000   0.1762
  -7.250  -0.4248   0.08697   0.08228  -0.0227   1.0000   0.1798
  -7.000  -0.4907   0.08618   0.08161  -0.0270   1.0000   0.1847
  -6.750  -0.4786   0.08262   0.07813  -0.0219   1.0000   0.1872
  -6.500  -0.4683   0.08091   0.07646  -0.0173   1.0000   0.1913
  -6.250  -0.5042   0.07811   0.07358  -0.0240   1.0000   0.2021
  -6.000  -0.4914   0.07562   0.07120  -0.0181   1.0000   0.2045
  -5.750  -0.4856   0.07404   0.06967  -0.0145   1.0000   0.2103
  -5.500  -0.4929   0.07060   0.06617  -0.0175   1.0000   0.2210
  -5.250  -0.4804   0.06867   0.06428  -0.0152   0.9989   0.2272
  -5.000  -0.4498   0.06441   0.05990  -0.0217   0.9926   0.2411
  -4.750  -0.4125   0.06143   0.05651  -0.0331   0.9840   0.2693
  -4.500  -0.3888   0.05723   0.05247  -0.0324   0.9789   0.2726
  -4.250  -0.3229   0.03686   0.02960  -0.0540   0.9746   0.1370
  -4.000  -0.2785   0.03291   0.02465  -0.0577   0.9707   0.1249
  -3.750  -0.2443   0.03110   0.02255  -0.0596   0.9640   0.1241
  -3.500  -0.2037   0.02944   0.02062  -0.0623   0.9584   0.1227
  -3.250  -0.1650   0.02812   0.01904  -0.0646   0.9526   0.1210
  -3.000  -0.1283   0.02708   0.01776  -0.0664   0.9454   0.1200
  -2.750  -0.0830   0.02619   0.01669  -0.0696   0.9407   0.1199
  -2.500  -0.0537   0.02565   0.01607  -0.0701   0.9315   0.1216
  -2.250  -0.0101   0.02502   0.01537  -0.0730   0.9260   0.1233
  -2.000   0.0201   0.02460   0.01494  -0.0735   0.9171   0.1240
  -1.750   0.0614   0.02408   0.01442  -0.0759   0.9108   0.1253
  -1.500   0.0925   0.02368   0.01413  -0.0766   0.9023   0.1274
  -1.250   0.1317   0.02327   0.01378  -0.0786   0.8953   0.1312
  -1.000   0.1648   0.02309   0.01361  -0.0796   0.8869   0.1377
  -0.750   0.2032   0.02272   0.01338  -0.0814   0.8795   0.1500
  -0.250   0.2751   0.02162   0.01316  -0.0844   0.8640   0.3377
   0.000   0.3093   0.01993   0.01310  -0.0841   0.8602   0.7636
   0.250   0.3641   0.01973   0.01309  -0.0885   0.8509   1.0000
   0.500   0.4072   0.01944   0.01265  -0.0905   0.8449   1.0000
   0.750   0.4318   0.01956   0.01266  -0.0897   0.8331   1.0000
   1.000   0.4747   0.01915   0.01212  -0.0915   0.8274   1.0000
   1.250   0.4977   0.01925   0.01214  -0.0902   0.8147   1.0000
   1.500   0.5267   0.01916   0.01197  -0.0898   0.8042   1.0000
   1.750   0.5635   0.01872   0.01144  -0.0903   0.7957   1.0000
   2.000   0.5886   0.01866   0.01132  -0.0892   0.7826   1.0000
   2.250   0.6168   0.01850   0.01109  -0.0885   0.7707   1.0000
   2.500   0.6526   0.01804   0.01054  -0.0887   0.7618   1.0000
   2.750   0.6764   0.01806   0.01054  -0.0875   0.7480   1.0000
   3.000   0.7017   0.01807   0.01052  -0.0864   0.7348   1.0000
   3.250   0.7290   0.01801   0.01041  -0.0857   0.7222   1.0000
   3.500   0.7587   0.01785   0.01020  -0.0852   0.7102   1.0000
   3.750   0.7865   0.01778   0.01008  -0.0845   0.6969   1.0000
   4.000   0.8115   0.01782   0.01010  -0.0834   0.6818   1.0000
   4.250   0.8369   0.01785   0.01012  -0.0824   0.6664   1.0000
   4.500   0.8624   0.01788   0.01013  -0.0814   0.6503   1.0000
   4.750   0.8881   0.01792   0.01013  -0.0805   0.6337   1.0000
   5.000   0.9138   0.01798   0.01015  -0.0795   0.6164   1.0000
   5.250   0.9394   0.01806   0.01017  -0.0785   0.5981   1.0000
   5.500   0.9615   0.01827   0.01039  -0.0771   0.5772   1.0000
   5.750   0.9850   0.01848   0.01057  -0.0759   0.5562   1.0000
   6.000   1.0096   0.01872   0.01070  -0.0748   0.5353   1.0000
   6.250   1.0315   0.01908   0.01103  -0.0735   0.5128   1.0000
   6.500   1.0537   0.01949   0.01139  -0.0722   0.4905   1.0000
   6.750   1.0770   0.01995   0.01173  -0.0711   0.4698   1.0000
   7.000   1.0983   0.02050   0.01225  -0.0698   0.4491   1.0000
   7.250   1.1195   0.02107   0.01281  -0.0686   0.4296   1.0000
   7.500   1.1403   0.02161   0.01332  -0.0672   0.4105   1.0000
   7.750   1.1602   0.02210   0.01373  -0.0658   0.3911   1.0000
   8.000   1.1782   0.02257   0.01411  -0.0640   0.3710   1.0000
   8.250   1.1930   0.02303   0.01462  -0.0619   0.3500   1.0000
   8.500   1.2081   0.02352   0.01509  -0.0598   0.3302   1.0000
   8.750   1.2237   0.02409   0.01565  -0.0579   0.3127   1.0000
   9.000   1.2390   0.02470   0.01629  -0.0559   0.2965   1.0000
   9.250   1.2525   0.02533   0.01695  -0.0538   0.2798   1.0000
   9.500   1.2635   0.02598   0.01765  -0.0513   0.2624   1.0000
   9.750   1.2703   0.02668   0.01845  -0.0482   0.2420   1.0000
  10.000   1.2703   0.02751   0.01931  -0.0443   0.2177   1.0000
  10.250   1.2643   0.02885   0.02060  -0.0400   0.1801   1.0000
  10.500   1.2523   0.03116   0.02257  -0.0357   0.1329   1.0000
  10.750   1.2449   0.03366   0.02480  -0.0324   0.1091   1.0000
  11.000   1.2421   0.03599   0.02702  -0.0298   0.0969   1.0000
  11.250   1.2402   0.03834   0.02928  -0.0275   0.0896   1.0000
  11.500   1.2441   0.04038   0.03138  -0.0255   0.0836   1.0000
  11.750   1.2471   0.04263   0.03347  -0.0236   0.0792   1.0000
  12.000   1.2561   0.04446   0.03547  -0.0221   0.0751   1.0000
  12.250   1.2650   0.04634   0.03734  -0.0207   0.0713   1.0000
  12.500   1.2828   0.04814   0.03901  -0.0193   0.0678   1.0000
  12.750   1.2975   0.05001   0.04109  -0.0180   0.0656   1.0000
  13.000   1.3117   0.05201   0.04324  -0.0169   0.0634   1.0000
  13.250   1.3268   0.05402   0.04529  -0.0159   0.0611   1.0000
  13.500   1.3566   0.05653   0.04771  -0.0156   0.0584   1.0000
  13.750   1.3564   0.05924   0.05075  -0.0141   0.0575   1.0000
  14.000   1.3566   0.06229   0.05410  -0.0127   0.0569   1.0000
  14.250   1.3530   0.06566   0.05777  -0.0115   0.0565   1.0000
  14.500   1.3452   0.06938   0.06179  -0.0105   0.0561   1.0000
  14.750   1.3334   0.07349   0.06619  -0.0099   0.0560   1.0000
  15.000   1.3179   0.07802   0.07101  -0.0097   0.0559   1.0000
  15.250   1.2990   0.08307   0.07633  -0.0102   0.0559   1.0000
  15.500   1.2769   0.08872   0.08225  -0.0113   0.0560   1.0000
  15.750   1.2522   0.09505   0.08885  -0.0134   0.0562   1.0000
  16.000   1.2253   0.10220   0.09624  -0.0164   0.0566   1.0000
  16.250   1.1967   0.11027   0.10454  -0.0205   0.0571   1.0000
  16.500   1.1673   0.11933   0.11379  -0.0256   0.0577   1.0000
  16.750   1.1393   0.12901   0.12361  -0.0313   0.0583   1.0000
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