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CLARK Z AIRFOIL (clarkz-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: CLARK Z AIRFOIL (clarkz-il)
Reynolds number: 100,000
Max Cl/Cd: 55.38 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarkz-il-100000-n5.txt
Download as CSV file: xf-clarkz-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3248   0.09932   0.09420  -0.0386   1.0000   0.0788
  -8.500  -0.3521   0.09789   0.09293  -0.0387   1.0000   0.0805
  -8.250  -0.3783   0.09668   0.09184  -0.0367   1.0000   0.0808
  -8.000  -0.3858   0.09229   0.08748  -0.0443   0.9936   0.0812
  -7.750  -0.3709   0.08579   0.08087  -0.0550   0.9844   0.0814
  -7.250  -0.3460   0.06588   0.06065  -0.0667   0.9717   0.0518
  -7.000  -0.3286   0.06217   0.05687  -0.0695   0.9636   0.0513
  -6.750  -0.3051   0.05725   0.05177  -0.0746   0.9584   0.0508
  -6.500  -0.2896   0.05209   0.04635  -0.0781   0.9486   0.0507
  -6.250  -0.2659   0.04588   0.03965  -0.0831   0.9430   0.0512
  -6.000  -0.2482   0.04185   0.03523  -0.0843   0.9337   0.0511
  -5.750  -0.2202   0.03801   0.03096  -0.0868   0.9290   0.0510
  -5.500  -0.1996   0.03515   0.02770  -0.0870   0.9202   0.0510
  -5.250  -0.1710   0.03234   0.02442  -0.0883   0.9147   0.0511
  -5.000  -0.1434   0.03007   0.02169  -0.0890   0.9085   0.0514
  -4.750  -0.1169   0.02830   0.01956  -0.0891   0.9010   0.0522
  -4.500  -0.0841   0.02707   0.01824  -0.0905   0.8965   0.0536
  -4.250  -0.0589   0.02611   0.01715  -0.0901   0.8880   0.0549
  -4.000  -0.0276   0.02486   0.01568  -0.0908   0.8822   0.0560
  -3.750   0.0017   0.02373   0.01433  -0.0909   0.8754   0.0569
  -3.500   0.0303   0.02274   0.01316  -0.0909   0.8677   0.0580
  -3.250   0.0639   0.02174   0.01198  -0.0916   0.8628   0.0593
  -3.000   0.0885   0.02106   0.01122  -0.0908   0.8527   0.0607
  -2.750   0.1203   0.02034   0.01054  -0.0914   0.8468   0.0635
  -2.500   0.1451   0.01988   0.01006  -0.0906   0.8367   0.0667
  -2.250   0.1765   0.01923   0.00931  -0.0909   0.8303   0.0699
  -2.000   0.2007   0.01876   0.00890  -0.0900   0.8198   0.0731
  -1.750   0.2307   0.01824   0.00834  -0.0901   0.8127   0.0785
  -1.500   0.2558   0.01787   0.00802  -0.0893   0.8022   0.0868
  -1.250   0.2838   0.01745   0.00764  -0.0891   0.7936   0.1027
  -1.000   0.3106   0.01702   0.00731  -0.0886   0.7839   0.1312
  -0.750   0.3370   0.01661   0.00709  -0.0882   0.7739   0.1832
  -0.500   0.3643   0.01583   0.00686  -0.0881   0.7651   0.3297
  -0.250   0.4033   0.01417   0.00702  -0.0887   0.7554   0.9365
   0.250   0.4775   0.01414   0.00659  -0.0920   0.7343   1.0000
   0.500   0.5021   0.01421   0.00651  -0.0911   0.7231   1.0000
   0.750   0.5284   0.01425   0.00638  -0.0905   0.7128   1.0000
   1.000   0.5527   0.01435   0.00636  -0.0896   0.7007   1.0000
   1.250   0.5774   0.01446   0.00636  -0.0888   0.6889   1.0000
   1.500   0.6030   0.01455   0.00632  -0.0881   0.6776   1.0000
   1.750   0.6284   0.01466   0.00631  -0.0874   0.6658   1.0000
   2.000   0.6528   0.01481   0.00638  -0.0866   0.6530   1.0000
   2.250   0.6777   0.01495   0.00643  -0.0859   0.6405   1.0000
   2.500   0.7031   0.01509   0.00647  -0.0852   0.6284   1.0000
   2.750   0.7283   0.01524   0.00654  -0.0845   0.6158   1.0000
   3.000   0.7526   0.01543   0.00667  -0.0837   0.6022   1.0000
   3.250   0.7771   0.01563   0.00680  -0.0829   0.5890   1.0000
   3.500   0.8018   0.01583   0.00694  -0.0822   0.5758   1.0000
   3.750   0.8265   0.01605   0.00707  -0.0814   0.5630   1.0000
   4.000   0.8510   0.01628   0.00724  -0.0807   0.5499   1.0000
   4.250   0.8749   0.01653   0.00747  -0.0799   0.5361   1.0000
   4.500   0.8989   0.01680   0.00770  -0.0791   0.5229   1.0000
   4.750   0.9228   0.01708   0.00793  -0.0783   0.5099   1.0000
   5.000   0.9467   0.01738   0.00818  -0.0775   0.4973   1.0000
   5.250   0.9703   0.01770   0.00845  -0.0767   0.4846   1.0000
   5.500   0.9932   0.01803   0.00877  -0.0758   0.4709   1.0000
   5.750   1.0156   0.01837   0.00909  -0.0748   0.4565   1.0000
   6.000   1.0373   0.01873   0.00940  -0.0737   0.4409   1.0000
   6.250   1.0579   0.01911   0.00972  -0.0724   0.4237   1.0000
   6.500   1.0780   0.01951   0.01007  -0.0711   0.4062   1.0000
   6.750   1.0982   0.01993   0.01046  -0.0698   0.3905   1.0000
   7.000   1.1188   0.02037   0.01090  -0.0687   0.3770   1.0000
   7.250   1.1391   0.02082   0.01135  -0.0675   0.3642   1.0000
   7.500   1.1587   0.02130   0.01183  -0.0662   0.3513   1.0000
   7.750   1.1776   0.02180   0.01233  -0.0649   0.3379   1.0000
   8.000   1.1958   0.02231   0.01288  -0.0634   0.3237   1.0000
   8.250   1.2132   0.02286   0.01347  -0.0619   0.3094   1.0000
   8.500   1.2296   0.02344   0.01408  -0.0603   0.2947   1.0000
   8.750   1.2448   0.02408   0.01473  -0.0585   0.2794   1.0000
   9.000   1.2578   0.02476   0.01542  -0.0564   0.2633   1.0000
   9.250   1.2687   0.02552   0.01618  -0.0541   0.2464   1.0000
   9.500   1.2782   0.02641   0.01705  -0.0517   0.2291   1.0000
   9.750   1.2865   0.02742   0.01802  -0.0493   0.2121   1.0000
  10.000   1.2943   0.02853   0.01911  -0.0470   0.1962   1.0000
  10.250   1.3008   0.02979   0.02033  -0.0448   0.1824   1.0000
  10.500   1.3073   0.03112   0.02166  -0.0427   0.1704   1.0000
  10.750   1.3139   0.03252   0.02309  -0.0407   0.1604   1.0000
  11.000   1.3185   0.03409   0.02464  -0.0388   0.1528   1.0000
  11.250   1.3254   0.03558   0.02620  -0.0371   0.1457   1.0000
  11.500   1.3291   0.03733   0.02794  -0.0354   0.1405   1.0000
  11.750   1.3369   0.03887   0.02958  -0.0340   0.1355   1.0000
  12.000   1.3433   0.04054   0.03134  -0.0326   0.1314   1.0000
  12.250   1.3484   0.04234   0.03317  -0.0313   0.1280   1.0000
  12.500   1.3550   0.04408   0.03495  -0.0301   0.1250   1.0000
  12.750   1.3630   0.04576   0.03677  -0.0290   0.1217   1.0000
  13.000   1.3695   0.04757   0.03868  -0.0280   0.1184   1.0000
  13.250   1.3746   0.04951   0.04068  -0.0271   0.1153   1.0000
  13.500   1.3802   0.05143   0.04260  -0.0261   0.1124   1.0000
  13.750   1.3850   0.05352   0.04490  -0.0254   0.1092   1.0000
  14.000   1.3883   0.05577   0.04728  -0.0248   0.1059   1.0000
  14.250   1.3900   0.05814   0.04973  -0.0244   0.1028   1.0000
  14.500   1.3927   0.06044   0.05201  -0.0238   0.0998   1.0000
  14.750   1.3921   0.06330   0.05514  -0.0237   0.0969   1.0000
  15.000   1.3913   0.06623   0.05823  -0.0237   0.0938   1.0000
  15.250   1.3901   0.06921   0.06131  -0.0238   0.0911   1.0000
  15.500   1.3903   0.07200   0.06410  -0.0239   0.0884   1.0000
  15.750   1.3857   0.07572   0.06806  -0.0245   0.0857   1.0000
  16.000   1.3804   0.07963   0.07218  -0.0254   0.0829   1.0000
  16.250   1.3754   0.08354   0.07622  -0.0264   0.0803   1.0000
  16.500   1.3713   0.08732   0.08008  -0.0274   0.0779   1.0000
  16.750   1.3668   0.09129   0.08418  -0.0285   0.0757   1.0000
  17.000   1.3575   0.09631   0.08947  -0.0303   0.0734   1.0000
  17.250   1.3483   0.10135   0.09470  -0.0323   0.0709   1.0000
  17.500   1.3402   0.10628   0.09976  -0.0343   0.0686   1.0000
  17.750   1.3346   0.11071   0.10422  -0.0362   0.0664   1.0000
  18.000   1.3197   0.11727   0.11106  -0.0394   0.0642   1.0000
  18.250   1.3049   0.12397   0.11798  -0.0427   0.0619   1.0000
  18.500   1.2923   0.13031   0.12447  -0.0461   0.0596   1.0000
  18.750   1.2855   0.13547   0.12967  -0.0490   0.0573   1.0000
  19.000   1.2638   0.14420   0.13863  -0.0540   0.0553   1.0000
  19.250   1.2372   0.15444   0.14910  -0.0602   0.0534   1.0000
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