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CLARK K AIRFOIL (clarkk-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: CLARK K AIRFOIL (clarkk-il)
Reynolds number: 500,000
Max Cl/Cd: 102.73 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkk-il-500000.txt
Download as CSV file: xf-clarkk-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4311   0.09364   0.09115  -0.0488   1.0000   0.0418
 -10.250  -0.4287   0.09033   0.08786  -0.0478   1.0000   0.0422
 -10.000  -0.4206   0.08862   0.08616  -0.0469   1.0000   0.0424
  -9.750  -0.4140   0.08684   0.08440  -0.0463   1.0000   0.0428
  -9.500  -0.4106   0.08489   0.08248  -0.0458   1.0000   0.0432
  -9.250  -0.4124   0.08269   0.08031  -0.0452   1.0000   0.0437
  -9.000  -0.4233   0.08046   0.07813  -0.0436   1.0000   0.0442
  -8.750  -0.4893   0.05452   0.05148  -0.0789   0.9852   0.0483
  -8.500  -0.4800   0.04547   0.04221  -0.0842   0.9825   0.0490
  -8.250  -0.4556   0.04335   0.04017  -0.0852   0.9784   0.0496
  -8.000  -0.4270   0.04169   0.03855  -0.0871   0.9756   0.0503
  -7.750  -0.3988   0.03939   0.03615  -0.0899   0.9731   0.0515
  -7.500  -0.3736   0.03813   0.03413  -0.0924   0.9679   0.0558
  -7.250  -0.3619   0.03231   0.02790  -0.0933   0.9603   0.0569
  -7.000  -0.3331   0.02983   0.02552  -0.0947   0.9571   0.0578
  -6.750  -0.3099   0.02827   0.02393  -0.0947   0.9505   0.0588
  -6.500  -0.2855   0.02684   0.02239  -0.0948   0.9440   0.0601
  -6.250  -0.2613   0.02583   0.02115  -0.0945   0.9376   0.0626
  -6.000  -0.2424   0.02433   0.01914  -0.0934   0.9288   0.0661
  -5.750  -0.2175   0.02250   0.01737  -0.0934   0.9228   0.0674
  -5.500  -0.1940   0.02139   0.01621  -0.0929   0.9145   0.0690
  -5.250  -0.1683   0.02058   0.01525  -0.0926   0.9082   0.0714
  -5.000  -0.1461   0.01954   0.01391  -0.0918   0.8991   0.0771
  -4.750  -0.1201   0.01830   0.01269  -0.0917   0.8926   0.0791
  -4.500  -0.0949   0.01762   0.01195  -0.0912   0.8839   0.0822
  -4.250  -0.0702   0.01658   0.01075  -0.0910   0.8768   0.0903
  -4.000  -0.0442   0.01593   0.01009  -0.0906   0.8682   0.0941
  -3.750  -0.0167   0.01571   0.00973  -0.0902   0.8608   0.0975
  -3.500   0.0156   0.01477   0.00828  -0.0889   0.8528   0.0638
  -3.250   0.0427   0.01399   0.00742  -0.0886   0.8451   0.0634
  -3.000   0.0697   0.01346   0.00683  -0.0883   0.8367   0.0635
  -2.750   0.0969   0.01286   0.00618  -0.0880   0.8289   0.0631
  -2.500   0.1239   0.01238   0.00566  -0.0877   0.8204   0.0629
  -2.250   0.1511   0.01197   0.00521  -0.0873   0.8123   0.0629
  -2.000   0.1780   0.01160   0.00483  -0.0870   0.8035   0.0630
  -1.750   0.2051   0.01129   0.00447  -0.0867   0.7953   0.0631
  -1.500   0.2320   0.01100   0.00418  -0.0864   0.7861   0.0634
  -1.250   0.2592   0.01081   0.00394  -0.0861   0.7778   0.0640
  -1.000   0.2863   0.01064   0.00377  -0.0858   0.7679   0.0646
  -0.750   0.3132   0.01043   0.00353  -0.0855   0.7590   0.0649
  -0.500   0.3395   0.01009   0.00319  -0.0851   0.7489   0.0655
  -0.250   0.3659   0.00985   0.00293  -0.0847   0.7383   0.0662
   0.000   0.3923   0.00967   0.00271  -0.0843   0.7263   0.0670
   0.250   0.4189   0.00954   0.00255  -0.0839   0.7135   0.0680
   0.500   0.4458   0.00943   0.00243  -0.0836   0.7020   0.0691
   0.750   0.4729   0.00936   0.00234  -0.0833   0.6916   0.0706
   1.000   0.4999   0.00933   0.00226  -0.0830   0.6806   0.0726
   1.250   0.5270   0.00930   0.00221  -0.0828   0.6687   0.0743
   1.500   0.5541   0.00929   0.00217  -0.0825   0.6574   0.0763
   1.750   0.5809   0.00930   0.00214  -0.0822   0.6456   0.0806
   2.000   0.6074   0.00923   0.00214  -0.0818   0.6325   0.1074
   2.250   0.6326   0.00887   0.00221  -0.0815   0.6193   0.2731
   2.500   0.6537   0.00798   0.00234  -0.0806   0.6069   0.6329
   2.750   0.6985   0.00735   0.00256  -0.0836   0.5917   0.9937
   3.000   0.7313   0.00749   0.00261  -0.0847   0.5761   1.0000
   3.250   0.7553   0.00764   0.00269  -0.0839   0.5614   1.0000
   3.500   0.7794   0.00780   0.00278  -0.0831   0.5470   1.0000
   3.750   0.8035   0.00797   0.00288  -0.0822   0.5320   1.0000
   4.000   0.8275   0.00816   0.00300  -0.0814   0.5160   1.0000
   4.250   0.8516   0.00835   0.00313  -0.0806   0.4994   1.0000
   4.500   0.8758   0.00855   0.00327  -0.0799   0.4830   1.0000
   4.750   0.8999   0.00876   0.00343  -0.0791   0.4657   1.0000
   5.000   0.9236   0.00900   0.00360  -0.0783   0.4448   1.0000
   5.250   0.9462   0.00932   0.00379  -0.0773   0.4202   1.0000
   5.500   0.9691   0.00963   0.00400  -0.0764   0.3938   1.0000
   5.750   0.9915   0.00999   0.00425  -0.0754   0.3686   1.0000
   6.000   1.0138   0.01036   0.00451  -0.0745   0.3439   1.0000
   6.250   1.0359   0.01076   0.00479  -0.0735   0.3197   1.0000
   6.500   1.0575   0.01119   0.00510  -0.0725   0.2954   1.0000
   6.750   1.0794   0.01161   0.00542  -0.0715   0.2747   1.0000
   7.000   1.1017   0.01199   0.00574  -0.0707   0.2576   1.0000
   7.250   1.1239   0.01238   0.00607  -0.0698   0.2417   1.0000
   7.500   1.1458   0.01278   0.00641  -0.0688   0.2264   1.0000
   7.750   1.1676   0.01319   0.00676  -0.0679   0.2127   1.0000
   8.000   1.1891   0.01360   0.00713  -0.0669   0.1986   1.0000
   8.250   1.2102   0.01404   0.00752  -0.0659   0.1818   1.0000
   8.500   1.2289   0.01463   0.00797  -0.0646   0.1564   1.0000
   8.750   1.2401   0.01572   0.00872  -0.0622   0.1037   1.0000
   9.000   1.2424   0.01730   0.00991  -0.0584   0.0525   1.0000
   9.250   1.2536   0.01823   0.01077  -0.0559   0.0412   1.0000
   9.500   1.2668   0.01904   0.01157  -0.0537   0.0369   1.0000
   9.750   1.2807   0.01981   0.01239  -0.0518   0.0342   1.0000
  10.000   1.2944   0.02059   0.01321  -0.0499   0.0322   1.0000
  10.250   1.3039   0.02166   0.01431  -0.0475   0.0304   1.0000
  10.500   1.3151   0.02263   0.01536  -0.0455   0.0293   1.0000
  10.750   1.3271   0.02357   0.01637  -0.0437   0.0283   1.0000
  11.000   1.3375   0.02464   0.01750  -0.0418   0.0273   1.0000
  11.250   1.3460   0.02588   0.01880  -0.0399   0.0264   1.0000
  11.500   1.3490   0.02757   0.02053  -0.0377   0.0255   1.0000
  11.750   1.3523   0.02932   0.02237  -0.0356   0.0248   1.0000
  12.000   1.3619   0.03063   0.02377  -0.0343   0.0242   1.0000
  12.250   1.3693   0.03217   0.02539  -0.0329   0.0236   1.0000
  12.500   1.3752   0.03388   0.02718  -0.0316   0.0230   1.0000
  12.750   1.3800   0.03575   0.02911  -0.0303   0.0225   1.0000
  13.000   1.3835   0.03778   0.03121  -0.0292   0.0220   1.0000
  13.250   1.3848   0.04009   0.03359  -0.0281   0.0216   1.0000
  13.500   1.3822   0.04282   0.03638  -0.0269   0.0211   1.0000
  13.750   1.3780   0.04576   0.03939  -0.0257   0.0208   1.0000
  14.000   1.3830   0.04790   0.04164  -0.0252   0.0205   1.0000
  14.250   1.3867   0.05023   0.04407  -0.0247   0.0201   1.0000
  14.500   1.3894   0.05272   0.04666  -0.0243   0.0197   1.0000
  14.750   1.3917   0.05532   0.04935  -0.0241   0.0193   1.0000
  15.000   1.3932   0.05805   0.05218  -0.0239   0.0189   1.0000
  15.250   1.3943   0.06089   0.05510  -0.0239   0.0186   1.0000
  15.500   1.3950   0.06383   0.05811  -0.0240   0.0183   1.0000
  15.750   1.3954   0.06684   0.06118  -0.0241   0.0180   1.0000
  16.000   1.3953   0.06986   0.06426  -0.0241   0.0178   1.0000
  16.250   1.3952   0.07280   0.06724  -0.0240   0.0175   1.0000
  16.500   1.3955   0.07532   0.06980  -0.0227   0.0171   1.0000
  16.750   1.3937   0.07894   0.07357  -0.0236   0.0170   1.0000
  17.000   1.3912   0.08268   0.07744  -0.0244   0.0168   1.0000
  17.250   1.3883   0.08651   0.08141  -0.0254   0.0167   1.0000
  17.500   1.3848   0.09047   0.08550  -0.0264   0.0165   1.0000
  17.750   1.3806   0.09460   0.08977  -0.0276   0.0163   1.0000
  18.000   1.3759   0.09886   0.09416  -0.0289   0.0161   1.0000
  18.250   1.3705   0.10329   0.09871  -0.0305   0.0159   1.0000
  18.500   1.3647   0.10786   0.10341  -0.0322   0.0158   1.0000
  18.750   1.3588   0.11256   0.10823  -0.0342   0.0156   1.0000
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