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


Details Polar file
Airfoil: CLARK Z AIRFOIL (clarkz-il)
Reynolds number: 200,000
Max Cl/Cd: 74.82 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkz-il-200000.txt
Download as CSV file: xf-clarkz-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK Z 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3510   0.09263   0.08919  -0.0331   1.0000   0.0642
  -8.000  -0.3674   0.09154   0.08819  -0.0298   1.0000   0.0648
  -7.750  -0.3853   0.09042   0.08714  -0.0268   0.9997   0.0654
  -7.500  -0.3707   0.08549   0.08221  -0.0357   0.9933   0.0684
  -7.250  -0.3504   0.07467   0.07126  -0.0578   0.9827   0.0717
  -7.000  -0.3296   0.07254   0.06915  -0.0569   0.9778   0.0728
  -6.750  -0.3039   0.06929   0.06588  -0.0604   0.9732   0.0747
  -6.500  -0.2773   0.06458   0.06107  -0.0679   0.9672   0.0784
  -6.250  -0.2536   0.05636   0.05250  -0.0799   0.9582   0.0835
  -6.000  -0.2216   0.05372   0.04988  -0.0825   0.9561   0.0852
  -5.750  -0.2002   0.05125   0.04735  -0.0839   0.9474   0.0879
  -5.500  -0.1666   0.04561   0.04121  -0.0914   0.9426   0.0965
  -5.250  -0.1312   0.04328   0.03895  -0.0941   0.9407   0.0993
  -5.000  -0.1100   0.04090   0.03601  -0.0956   0.9296   0.1099
  -4.750  -0.0777   0.03768   0.03289  -0.0978   0.9267   0.1120
  -4.500  -0.0578   0.02804   0.02190  -0.0972   0.9169   0.0726
  -4.250  -0.0238   0.02879   0.02299  -0.0991   0.9122   0.0865
  -4.000   0.0081   0.02296   0.01611  -0.0990   0.9079   0.0663
  -3.750   0.0326   0.02149   0.01437  -0.0981   0.8985   0.0661
  -3.500   0.0659   0.01988   0.01247  -0.0986   0.8938   0.0656
  -3.250   0.0916   0.01887   0.01128  -0.0978   0.8846   0.0659
  -3.000   0.1226   0.01786   0.01012  -0.0978   0.8785   0.0669
  -2.750   0.1494   0.01712   0.00929  -0.0972   0.8698   0.0681
  -2.500   0.1788   0.01651   0.00856  -0.0969   0.8624   0.0703
  -2.250   0.2047   0.01569   0.00778  -0.0963   0.8535   0.0732
  -2.000   0.2328   0.01511   0.00721  -0.0959   0.8456   0.0765
  -1.750   0.2587   0.01468   0.00676  -0.0951   0.8359   0.0803
  -1.500   0.2864   0.01407   0.00616  -0.0946   0.8280   0.0863
  -1.250   0.3115   0.01370   0.00584  -0.0938   0.8175   0.0975
  -1.000   0.3389   0.01312   0.00539  -0.0933   0.8095   0.1320
  -0.750   0.3620   0.01237   0.00514  -0.0925   0.7987   0.2489
  -0.500   0.3764   0.01087   0.00514  -0.0899   0.7895   0.6668
  -0.250   0.4531   0.01026   0.00505  -0.0980   0.7811   0.9951
   0.000   0.4847   0.01027   0.00491  -0.0986   0.7703   1.0000
   0.250   0.5106   0.01029   0.00475  -0.0979   0.7606   1.0000
   0.500   0.5343   0.01035   0.00471  -0.0969   0.7484   1.0000
   0.750   0.5587   0.01042   0.00466  -0.0961   0.7369   1.0000
   1.000   0.5842   0.01048   0.00458  -0.0953   0.7262   1.0000
   1.250   0.6085   0.01055   0.00456  -0.0944   0.7139   1.0000
   1.500   0.6327   0.01065   0.00457  -0.0935   0.7014   1.0000
   1.750   0.6575   0.01075   0.00457  -0.0926   0.6893   1.0000
   2.000   0.6828   0.01086   0.00456  -0.0919   0.6773   1.0000
   2.250   0.7071   0.01097   0.00459  -0.0910   0.6639   1.0000
   2.500   0.7313   0.01110   0.00466  -0.0901   0.6501   1.0000
   2.750   0.7558   0.01124   0.00473  -0.0893   0.6363   1.0000
   3.000   0.7804   0.01139   0.00479  -0.0884   0.6224   1.0000
   3.250   0.8051   0.01156   0.00487  -0.0876   0.6085   1.0000
   3.500   0.8297   0.01174   0.00497  -0.0868   0.5944   1.0000
   3.750   0.8542   0.01194   0.00507  -0.0860   0.5800   1.0000
   4.000   0.8782   0.01214   0.00522  -0.0852   0.5650   1.0000
   4.250   0.9021   0.01236   0.00538  -0.0843   0.5497   1.0000
   4.500   0.9258   0.01258   0.00554  -0.0834   0.5339   1.0000
   4.750   0.9491   0.01282   0.00570  -0.0825   0.5176   1.0000
   5.000   0.9722   0.01307   0.00588  -0.0815   0.5011   1.0000
   5.250   0.9952   0.01334   0.00608  -0.0805   0.4849   1.0000
   5.500   1.0179   0.01362   0.00630  -0.0796   0.4689   1.0000
   5.750   1.0407   0.01391   0.00655  -0.0786   0.4536   1.0000
   6.000   1.0637   0.01422   0.00682  -0.0777   0.4398   1.0000
   6.250   1.0866   0.01454   0.00712  -0.0769   0.4270   1.0000
   6.500   1.1094   0.01490   0.00743  -0.0760   0.4148   1.0000
   6.750   1.1317   0.01525   0.00774  -0.0750   0.4020   1.0000
   7.000   1.1537   0.01557   0.00808  -0.0740   0.3887   1.0000
   7.250   1.1754   0.01592   0.00844  -0.0730   0.3756   1.0000
   7.500   1.1967   0.01629   0.00881  -0.0719   0.3629   1.0000
   7.750   1.2173   0.01668   0.00919  -0.0708   0.3499   1.0000
   8.000   1.2369   0.01710   0.00958  -0.0694   0.3360   1.0000
   8.250   1.2557   0.01752   0.01001  -0.0680   0.3210   1.0000
   8.500   1.2735   0.01796   0.01046  -0.0664   0.3045   1.0000
   8.750   1.2903   0.01843   0.01095  -0.0647   0.2861   1.0000
   9.000   1.3050   0.01899   0.01149  -0.0627   0.2648   1.0000
   9.250   1.3151   0.01971   0.01213  -0.0600   0.2410   1.0000
   9.500   1.3218   0.02064   0.01293  -0.0570   0.2143   1.0000
   9.750   1.3280   0.02175   0.01390  -0.0540   0.1901   1.0000
  10.000   1.3337   0.02297   0.01501  -0.0512   0.1730   1.0000
  10.250   1.3412   0.02417   0.01615  -0.0488   0.1609   1.0000
  10.500   1.3485   0.02544   0.01738  -0.0464   0.1525   1.0000
  10.750   1.3581   0.02660   0.01855  -0.0445   0.1453   1.0000
  11.000   1.3663   0.02793   0.01984  -0.0425   0.1397   1.0000
  11.250   1.3778   0.02902   0.02101  -0.0409   0.1343   1.0000
  11.500   1.3861   0.03037   0.02232  -0.0392   0.1295   1.0000
  11.750   1.3965   0.03164   0.02365  -0.0377   0.1252   1.0000
  12.000   1.4070   0.03285   0.02495  -0.0363   0.1210   1.0000
  12.250   1.4158   0.03423   0.02634  -0.0349   0.1172   1.0000
  12.500   1.4258   0.03567   0.02776  -0.0335   0.1138   1.0000
  12.750   1.4356   0.03700   0.02924  -0.0323   0.1108   1.0000
  13.000   1.4447   0.03841   0.03076  -0.0312   0.1077   1.0000
  13.250   1.4524   0.03995   0.03233  -0.0301   0.1046   1.0000
  13.500   1.4615   0.04153   0.03388  -0.0289   0.1013   1.0000
  13.750   1.4670   0.04326   0.03581  -0.0279   0.0986   1.0000
  14.000   1.4726   0.04504   0.03771  -0.0271   0.0956   1.0000
  14.250   1.4776   0.04690   0.03964  -0.0263   0.0929   1.0000
  14.500   1.4858   0.04861   0.04129  -0.0252   0.0897   1.0000
  14.750   1.4868   0.05091   0.04383  -0.0247   0.0875   1.0000
  15.000   1.4883   0.05326   0.04634  -0.0243   0.0847   1.0000
  15.250   1.4892   0.05571   0.04888  -0.0240   0.0818   1.0000
  15.500   1.4920   0.05797   0.05110  -0.0234   0.0785   1.0000
  15.750   1.4875   0.06133   0.05474  -0.0238   0.0757   1.0000
  16.000   1.4841   0.06468   0.05824  -0.0244   0.0723   1.0000
  16.250   1.4802   0.06805   0.06160  -0.0248   0.0689   1.0000
  16.500   1.4728   0.07230   0.06610  -0.0259   0.0650   1.0000
  16.750   1.4655   0.07666   0.07058  -0.0273   0.0611   1.0000
  17.000   1.4561   0.08135   0.07537  -0.0286   0.0571   1.0000
  17.250   1.4470   0.08623   0.08037  -0.0303   0.0532   1.0000
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