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CLARK Z AIRFOIL (clarkz-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: CLARK Z AIRFOIL (clarkz-il)
Reynolds number: 50,000
Max Cl/Cd: 36.2 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarkz-il-50000-n5.txt
Download as CSV file: xf-clarkz-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3233   0.11293   0.10557  -0.0366   1.0000   0.1390
  -9.000  -0.3430   0.11204   0.10483  -0.0378   1.0000   0.1403
  -8.750  -0.3610   0.11075   0.10371  -0.0378   1.0000   0.1407
  -8.500  -0.3629   0.10762   0.10069  -0.0366   1.0000   0.1413
  -8.250  -0.3452   0.10326   0.09633  -0.0347   1.0000   0.1427
  -8.000  -0.3386   0.10046   0.09357  -0.0326   1.0000   0.1450
  -7.750  -0.3432   0.09850   0.09170  -0.0306   1.0000   0.1472
  -7.500  -0.3552   0.09693   0.09024  -0.0282   1.0000   0.1491
  -7.000  -0.4197   0.08725   0.08067  -0.0344   1.0000   0.0951
  -6.750  -0.4121   0.08619   0.07970  -0.0297   1.0000   0.0983
  -6.250  -0.4091   0.07329   0.06640  -0.0422   0.9923   0.0809
  -6.000  -0.3859   0.06940   0.06243  -0.0454   0.9856   0.0797
  -5.750  -0.3626   0.06502   0.05789  -0.0496   0.9781   0.0783
  -5.500  -0.3357   0.06028   0.05289  -0.0546   0.9713   0.0770
  -5.250  -0.3119   0.05602   0.04832  -0.0583   0.9629   0.0763
  -5.000  -0.2832   0.05207   0.04399  -0.0621   0.9560   0.0771
  -4.750  -0.2558   0.04858   0.04009  -0.0649   0.9481   0.0779
  -4.500  -0.2240   0.04527   0.03632  -0.0679   0.9418   0.0782
  -4.250  -0.1960   0.04251   0.03313  -0.0695   0.9337   0.0782
  -4.000  -0.1594   0.03986   0.02999  -0.0723   0.9284   0.0786
  -3.750  -0.1325   0.03789   0.02760  -0.0729   0.9196   0.0792
  -3.500  -0.0953   0.03595   0.02509  -0.0750   0.9137   0.0813
  -3.250  -0.0668   0.03475   0.02382  -0.0757   0.9054   0.0838
  -3.000  -0.0317   0.03357   0.02247  -0.0773   0.8986   0.0867
  -2.750   0.0014   0.03241   0.02106  -0.0783   0.8912   0.0891
  -2.250   0.0735   0.03035   0.01861  -0.0810   0.8776   0.0966
  -2.000   0.1023   0.02977   0.01799  -0.0811   0.8679   0.1030
  -1.750   0.1433   0.02889   0.01698  -0.0830   0.8628   0.1113
  -1.500   0.1684   0.02844   0.01650  -0.0824   0.8517   0.1208
  -1.250   0.2051   0.02772   0.01574  -0.0836   0.8451   0.1400
  -1.000   0.2318   0.02714   0.01533  -0.0834   0.8346   0.1683
  -0.750   0.2635   0.02620   0.01479  -0.0842   0.8265   0.2391
  -0.500   0.2909   0.02368   0.01477  -0.0826   0.8189   0.8504
  -0.250   0.3396   0.02352   0.01421  -0.0860   0.8107   1.0000
   0.000   0.3678   0.02359   0.01399  -0.0857   0.8001   1.0000
   0.250   0.3934   0.02373   0.01390  -0.0851   0.7887   1.0000
   0.500   0.4286   0.02360   0.01354  -0.0858   0.7809   1.0000
   0.750   0.4512   0.02381   0.01359  -0.0847   0.7681   1.0000
   1.000   0.4777   0.02393   0.01355  -0.0841   0.7570   1.0000
   1.250   0.5105   0.02383   0.01329  -0.0844   0.7482   1.0000
   1.500   0.5334   0.02406   0.01340  -0.0833   0.7353   1.0000
   1.750   0.5596   0.02418   0.01342  -0.0827   0.7239   1.0000
   2.000   0.5917   0.02409   0.01321  -0.0828   0.7147   1.0000
   2.250   0.6144   0.02435   0.01340  -0.0817   0.7015   1.0000
   2.500   0.6395   0.02454   0.01352  -0.0809   0.6894   1.0000
   2.750   0.6696   0.02452   0.01341  -0.0807   0.6793   1.0000
   3.000   0.6946   0.02472   0.01356  -0.0799   0.6668   1.0000
   3.250   0.7180   0.02500   0.01381  -0.0790   0.6538   1.0000
   3.500   0.7439   0.02519   0.01395  -0.0783   0.6418   1.0000
   3.750   0.7742   0.02518   0.01389  -0.0781   0.6315   1.0000
   4.000   0.7961   0.02556   0.01426  -0.0770   0.6178   1.0000
   4.250   0.8194   0.02590   0.01459  -0.0760   0.6048   1.0000
   4.500   0.8447   0.02616   0.01485  -0.0753   0.5929   1.0000
   4.750   0.8737   0.02624   0.01489  -0.0750   0.5820   1.0000
   5.000   0.8949   0.02672   0.01539  -0.0739   0.5685   1.0000
   5.250   0.9173   0.02715   0.01586  -0.0729   0.5558   1.0000
   5.500   0.9419   0.02749   0.01621  -0.0721   0.5438   1.0000
   5.750   0.9696   0.02768   0.01637  -0.0716   0.5328   1.0000
   6.000   0.9896   0.02824   0.01701  -0.0704   0.5195   1.0000
   6.250   1.0109   0.02876   0.01757  -0.0693   0.5068   1.0000
   6.500   1.0339   0.02918   0.01802  -0.0683   0.4945   1.0000
   6.750   1.0591   0.02948   0.01832  -0.0676   0.4825   1.0000
   7.000   1.0796   0.02997   0.01887  -0.0663   0.4689   1.0000
   7.250   1.0982   0.03046   0.01939  -0.0647   0.4539   1.0000
   7.500   1.1163   0.03087   0.01980  -0.0630   0.4376   1.0000
   7.750   1.1332   0.03130   0.02025  -0.0611   0.4207   1.0000
   8.000   1.1488   0.03181   0.02076  -0.0592   0.4041   1.0000
   8.250   1.1632   0.03243   0.02141  -0.0572   0.3881   1.0000
   8.500   1.1766   0.03316   0.02219  -0.0552   0.3729   1.0000
   8.750   1.1891   0.03394   0.02306  -0.0531   0.3581   1.0000
   9.000   1.2003   0.03478   0.02397  -0.0509   0.3433   1.0000
   9.250   1.2092   0.03567   0.02491  -0.0485   0.3287   1.0000
   9.500   1.2172   0.03667   0.02595  -0.0460   0.3138   1.0000
   9.750   1.2244   0.03777   0.02710  -0.0437   0.2989   1.0000
  10.000   1.2304   0.03901   0.02839  -0.0414   0.2839   1.0000
  10.250   1.2353   0.04038   0.02980  -0.0392   0.2689   1.0000
  10.500   1.2396   0.04189   0.03132  -0.0372   0.2544   1.0000
  10.750   1.2438   0.04349   0.03292  -0.0353   0.2409   1.0000
  11.000   1.2478   0.04524   0.03469  -0.0335   0.2283   1.0000
  11.500   1.2556   0.04917   0.03874  -0.0306   0.2063   1.0000
  11.750   1.2621   0.05090   0.04041  -0.0293   0.1976   1.0000
  12.000   1.2647   0.05328   0.04294  -0.0282   0.1889   1.0000
  12.250   1.2732   0.05499   0.04458  -0.0270   0.1822   1.0000
  12.500   1.2763   0.05753   0.04733  -0.0262   0.1758   1.0000
  12.750   1.2854   0.05934   0.04919  -0.0252   0.1704   1.0000
  13.000   1.2910   0.06167   0.05165  -0.0244   0.1655   1.0000
  13.250   1.2915   0.06459   0.05477  -0.0238   0.1608   1.0000
  13.500   1.2999   0.06656   0.05680  -0.0230   0.1564   1.0000
  13.750   1.3069   0.06884   0.05917  -0.0224   0.1526   1.0000
  14.000   1.2981   0.07307   0.06370  -0.0224   0.1497   1.0000
  14.250   1.2904   0.07725   0.06812  -0.0226   0.1468   1.0000
  14.500   1.2875   0.08084   0.07189  -0.0226   0.1439   1.0000
  14.750   1.3133   0.08080   0.07176  -0.0212   0.1400   1.0000
  15.000   1.2808   0.08839   0.07971  -0.0232   0.1385   1.0000
  15.250   1.2340   0.09902   0.09066  -0.0274   0.1374   1.0000
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