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


Details Polar file
Airfoil: CLARK X AIRFOIL (clarkx-il)
Reynolds number: 100,000
Max Cl/Cd: 55.22 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarkx-il-100000-n5.txt
Download as CSV file: xf-clarkx-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK X 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4197   0.09161   0.08630  -0.0454   1.0000   0.0543
  -9.500  -0.4281   0.08710   0.08187  -0.0469   1.0000   0.0544
  -9.250  -0.4414   0.08248   0.07733  -0.0483   1.0000   0.0543
  -9.000  -0.4623   0.07782   0.07278  -0.0491   1.0000   0.0542
  -8.750  -0.4976   0.07291   0.06801  -0.0494   1.0000   0.0538
  -8.500  -0.5371   0.06522   0.06034  -0.0517   1.0000   0.0533
  -8.250  -0.5709   0.05815   0.05312  -0.0520   1.0000   0.0531
  -8.000  -0.5631   0.05144   0.04602  -0.0574   0.9938   0.0546
  -7.750  -0.5491   0.04516   0.03917  -0.0620   0.9864   0.0567
  -7.500  -0.5316   0.03986   0.03319  -0.0649   0.9796   0.0581
  -7.250  -0.5075   0.03583   0.02846  -0.0672   0.9741   0.0594
  -7.000  -0.4831   0.03312   0.02520  -0.0684   0.9680   0.0609
  -6.750  -0.4531   0.03168   0.02368  -0.0699   0.9632   0.0628
  -6.500  -0.4214   0.03026   0.02204  -0.0716   0.9590   0.0648
  -6.250  -0.3946   0.02875   0.02023  -0.0722   0.9524   0.0664
  -6.000  -0.3616   0.02723   0.01840  -0.0738   0.9483   0.0684
  -5.750  -0.3299   0.02592   0.01678  -0.0749   0.9436   0.0705
  -5.500  -0.3006   0.02491   0.01547  -0.0754   0.9372   0.0732
  -5.250  -0.2665   0.02391   0.01449  -0.0772   0.9332   0.0763
  -5.000  -0.2338   0.02309   0.01359  -0.0783   0.9285   0.0794
  -4.750  -0.2054   0.02233   0.01270  -0.0785   0.9216   0.0825
  -4.500  -0.1710   0.02159   0.01176  -0.0798   0.9173   0.0862
  -4.250  -0.1423   0.02092   0.01119  -0.0803   0.9110   0.0910
  -4.000  -0.1124   0.02040   0.01061  -0.0807   0.9045   0.0970
  -3.750  -0.0784   0.01974   0.00993  -0.0819   0.9003   0.1029
  -3.500  -0.0529   0.01935   0.00955  -0.0816   0.8920   0.1102
  -3.250  -0.0212   0.01885   0.00905  -0.0823   0.8866   0.1204
  -3.000   0.0069   0.01844   0.00864  -0.0823   0.8797   0.1320
  -2.750   0.0359   0.01798   0.00823  -0.0826   0.8729   0.1488
  -2.500   0.0663   0.01748   0.00784  -0.0831   0.8672   0.1749
  -2.250   0.0921   0.01707   0.00765  -0.0827   0.8589   0.2144
  -2.000   0.1237   0.01661   0.00740  -0.0834   0.8539   0.2826
  -1.750   0.1479   0.01634   0.00731  -0.0827   0.8446   0.3371
  -1.500   0.1783   0.01587   0.00708  -0.0830   0.8390   0.4057
  -1.250   0.2019   0.01550   0.00704  -0.0822   0.8297   0.4931
  -1.000   0.2279   0.01485   0.00695  -0.0811   0.8238   0.6424
  -0.750   0.2555   0.01445   0.00711  -0.0796   0.8153   0.8362
  -0.500   0.3169   0.01424   0.00691  -0.0855   0.8102   0.9630
  -0.250   0.3666   0.01417   0.00670  -0.0900   0.8022   1.0000
   0.000   0.3932   0.01413   0.00652  -0.0895   0.7934   1.0000
   0.250   0.4160   0.01419   0.00648  -0.0885   0.7824   1.0000
   0.500   0.4415   0.01419   0.00637  -0.0878   0.7727   1.0000
   0.750   0.4673   0.01420   0.00626  -0.0872   0.7626   1.0000
   1.000   0.4909   0.01427   0.00627  -0.0862   0.7513   1.0000
   1.250   0.5164   0.01432   0.00622  -0.0856   0.7410   1.0000
   1.500   0.5426   0.01436   0.00617  -0.0850   0.7308   1.0000
   1.750   0.5665   0.01446   0.00624  -0.0841   0.7191   1.0000
   2.000   0.5915   0.01455   0.00627  -0.0834   0.7079   1.0000
   2.250   0.6177   0.01462   0.00626  -0.0828   0.6972   1.0000
   2.500   0.6424   0.01473   0.00634  -0.0821   0.6850   1.0000
   2.750   0.6668   0.01485   0.00643  -0.0812   0.6721   1.0000
   3.000   0.6916   0.01498   0.00653  -0.0805   0.6590   1.0000
   3.250   0.7163   0.01510   0.00662  -0.0797   0.6453   1.0000
   3.500   0.7408   0.01523   0.00671  -0.0788   0.6303   1.0000
   3.750   0.7650   0.01537   0.00683  -0.0779   0.6143   1.0000
   4.000   0.7891   0.01553   0.00695  -0.0770   0.5977   1.0000
   4.250   0.8130   0.01571   0.00709  -0.0761   0.5810   1.0000
   4.500   0.8368   0.01592   0.00728  -0.0752   0.5644   1.0000
   4.750   0.8604   0.01615   0.00748  -0.0743   0.5478   1.0000
   5.000   0.8839   0.01640   0.00771  -0.0734   0.5311   1.0000
   5.250   0.9071   0.01667   0.00795  -0.0724   0.5141   1.0000
   5.500   0.9299   0.01697   0.00825  -0.0714   0.4966   1.0000
   5.750   0.9522   0.01730   0.00857  -0.0704   0.4782   1.0000
   6.000   0.9743   0.01766   0.00892  -0.0693   0.4601   1.0000
   6.250   0.9962   0.01804   0.00932  -0.0682   0.4426   1.0000
   6.500   1.0177   0.01845   0.00972  -0.0671   0.4250   1.0000
   6.750   1.0386   0.01890   0.01015  -0.0659   0.4074   1.0000
   7.000   1.0592   0.01938   0.01061  -0.0647   0.3904   1.0000
   7.250   1.0797   0.01988   0.01114  -0.0635   0.3746   1.0000
   7.500   1.0999   0.02041   0.01169  -0.0622   0.3594   1.0000
   7.750   1.1192   0.02098   0.01227  -0.0609   0.3436   1.0000
   8.000   1.1367   0.02158   0.01287  -0.0593   0.3248   1.0000
   8.250   1.1520   0.02222   0.01349  -0.0574   0.3031   1.0000
   8.500   1.1652   0.02294   0.01415  -0.0553   0.2800   1.0000
   8.750   1.1777   0.02368   0.01486  -0.0531   0.2560   1.0000
   9.000   1.1890   0.02448   0.01560  -0.0509   0.2336   1.0000
   9.250   1.1991   0.02531   0.01641  -0.0485   0.2122   1.0000
   9.500   1.2084   0.02626   0.01732  -0.0461   0.1922   1.0000
   9.750   1.2178   0.02730   0.01836  -0.0438   0.1692   1.0000
  10.000   1.2244   0.02856   0.01956  -0.0414   0.1402   1.0000
  10.250   1.2259   0.03028   0.02105  -0.0388   0.0997   1.0000
  10.500   1.2229   0.03248   0.02298  -0.0360   0.0732   1.0000
  10.750   1.2226   0.03459   0.02502  -0.0336   0.0590   1.0000
  11.000   1.2224   0.03674   0.02717  -0.0315   0.0513   1.0000
  11.250   1.2237   0.03884   0.02937  -0.0296   0.0468   1.0000
  11.500   1.2231   0.04118   0.03179  -0.0280   0.0436   1.0000
  11.750   1.2198   0.04386   0.03453  -0.0265   0.0412   1.0000
  12.000   1.2198   0.04633   0.03720  -0.0254   0.0389   1.0000
  12.250   1.2181   0.04906   0.04006  -0.0245   0.0370   1.0000
  12.500   1.2147   0.05205   0.04317  -0.0238   0.0355   1.0000
  12.750   1.2092   0.05538   0.04659  -0.0232   0.0344   1.0000
  13.000   1.2041   0.05874   0.05005  -0.0228   0.0335   1.0000
  13.250   1.2027   0.06178   0.05326  -0.0225   0.0326   1.0000
  13.500   1.2014   0.06490   0.05652  -0.0222   0.0315   1.0000
  13.750   1.2001   0.06808   0.05983  -0.0222   0.0305   1.0000
  14.000   1.1987   0.07133   0.06319  -0.0222   0.0295   1.0000
  14.250   1.1971   0.07464   0.06658  -0.0224   0.0286   1.0000
  14.500   1.1962   0.07786   0.06984  -0.0225   0.0277   1.0000
  14.750   1.1975   0.08074   0.07277  -0.0222   0.0269   1.0000
  15.000   1.1992   0.08381   0.07602  -0.0222   0.0264   1.0000
  15.250   1.2007   0.08697   0.07936  -0.0223   0.0258   1.0000
  15.500   1.2009   0.09040   0.08296  -0.0226   0.0253   1.0000
  15.750   1.1996   0.09414   0.08687  -0.0232   0.0248   1.0000
  16.000   1.1964   0.09825   0.09116  -0.0243   0.0243   1.0000
  16.250   1.1920   0.10266   0.09574  -0.0257   0.0238   1.0000
  16.500   1.1868   0.10730   0.10055  -0.0274   0.0234   1.0000
  16.750   1.1806   0.11222   0.10563  -0.0295   0.0229   1.0000
  17.000   1.1742   0.11730   0.11086  -0.0318   0.0226   1.0000
  17.250   1.1677   0.12247   0.11616  -0.0343   0.0223   1.0000
  17.500   1.1615   0.12768   0.12149  -0.0369   0.0219   1.0000
  17.750   1.1542   0.13329   0.12723  -0.0399   0.0217   1.0000
  18.250   1.1326   0.14687   0.14113  -0.0480   0.0214   1.0000
  18.500   1.1116   0.15712   0.15163  -0.0550   0.0216   1.0000
  18.750   1.0022   0.20287   0.19777  -0.0830   0.0240   1.0000
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