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CLARK K AIRFOIL (clarkk-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: CLARK K AIRFOIL (clarkk-il)
Reynolds number: 500,000
Max Cl/Cd: 91.27 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarkk-il-500000-n5.txt
Download as CSV file: xf-clarkk-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7985   0.03391   0.03025  -0.0813   0.9907   0.0326
 -11.000  -0.7684   0.03392   0.03024  -0.0824   0.9881   0.0329
 -10.750  -0.7373   0.03394   0.03025  -0.0837   0.9860   0.0331
 -10.500  -0.7063   0.03377   0.03005  -0.0851   0.9842   0.0334
 -10.250  -0.6800   0.03340   0.02964  -0.0857   0.9798   0.0339
 -10.000  -0.6530   0.03268   0.02884  -0.0868   0.9762   0.0344
  -9.750  -0.6272   0.03152   0.02754  -0.0879   0.9726   0.0352
  -9.500  -0.6068   0.02972   0.02549  -0.0883   0.9663   0.0364
  -9.250  -0.5904   0.02635   0.02151  -0.0886   0.9602   0.0384
  -9.000  -0.5660   0.02549   0.02058  -0.0887   0.9542   0.0388
  -8.750  -0.5389   0.02483   0.01986  -0.0892   0.9498   0.0391
  -8.500  -0.5146   0.02428   0.01924  -0.0890   0.9429   0.0395
  -8.250  -0.4885   0.02368   0.01855  -0.0892   0.9374   0.0399
  -8.000  -0.4645   0.02300   0.01779  -0.0889   0.9300   0.0403
  -7.750  -0.4396   0.02217   0.01682  -0.0888   0.9236   0.0408
  -7.500  -0.4155   0.02139   0.01591  -0.0884   0.9158   0.0414
  -7.250  -0.3905   0.02063   0.01500  -0.0881   0.9086   0.0421
  -7.000  -0.3661   0.01979   0.01400  -0.0877   0.9004   0.0427
  -6.750  -0.3410   0.01897   0.01300  -0.0874   0.8925   0.0432
  -6.500  -0.3158   0.01824   0.01211  -0.0870   0.8839   0.0437
  -6.250  -0.2900   0.01764   0.01135  -0.0867   0.8757   0.0442
  -6.000  -0.2638   0.01724   0.01081  -0.0863   0.8671   0.0447
  -5.750  -0.2375   0.01682   0.01025  -0.0861   0.8589   0.0449
  -5.500  -0.2117   0.01597   0.00931  -0.0858   0.8504   0.0452
  -5.250  -0.1856   0.01521   0.00848  -0.0856   0.8423   0.0455
  -5.000  -0.1592   0.01465   0.00787  -0.0854   0.8340   0.0458
  -4.750  -0.1326   0.01418   0.00735  -0.0852   0.8257   0.0461
  -4.500  -0.1058   0.01376   0.00689  -0.0850   0.8173   0.0464
  -4.250  -0.0791   0.01338   0.00645  -0.0848   0.8090   0.0467
  -4.000  -0.0522   0.01302   0.00606  -0.0846   0.8006   0.0471
  -3.750  -0.0253   0.01270   0.00569  -0.0844   0.7923   0.0475
  -3.500   0.0018   0.01242   0.00538  -0.0842   0.7839   0.0480
  -3.250   0.0287   0.01216   0.00507  -0.0840   0.7755   0.0486
  -3.000   0.0557   0.01187   0.00475  -0.0838   0.7671   0.0490
  -2.500   0.1097   0.01136   0.00418  -0.0834   0.7501   0.0498
  -2.250   0.1366   0.01116   0.00392  -0.0831   0.7415   0.0503
  -2.000   0.1637   0.01095   0.00369  -0.0830   0.7325   0.0507
  -1.750   0.1906   0.01077   0.00348  -0.0827   0.7238   0.0511
  -1.500   0.2178   0.01061   0.00330  -0.0825   0.7143   0.0514
  -1.250   0.2448   0.01047   0.00313  -0.0823   0.7050   0.0518
  -1.000   0.2718   0.01035   0.00298  -0.0821   0.6948   0.0521
  -0.750   0.2989   0.01024   0.00285  -0.0819   0.6845   0.0524
  -0.500   0.3259   0.01017   0.00274  -0.0816   0.6738   0.0526
  -0.250   0.3521   0.00996   0.00250  -0.0813   0.6604   0.0535
   0.000   0.3783   0.00987   0.00236  -0.0809   0.6434   0.0545
   0.250   0.4046   0.00983   0.00227  -0.0806   0.6257   0.0555
   0.500   0.4313   0.00979   0.00220  -0.0803   0.6111   0.0562
   0.750   0.4583   0.00977   0.00214  -0.0801   0.5980   0.0570
   1.000   0.4850   0.00977   0.00211  -0.0798   0.5843   0.0579
   1.250   0.5117   0.00980   0.00209  -0.0795   0.5702   0.0587
   1.500   0.5383   0.00984   0.00209  -0.0792   0.5571   0.0596
   1.750   0.5649   0.00989   0.00210  -0.0789   0.5434   0.0604
   2.000   0.5913   0.00997   0.00212  -0.0786   0.5287   0.0612
   2.250   0.6178   0.01003   0.00215  -0.0783   0.5142   0.0626
   2.500   0.6444   0.01010   0.00219  -0.0781   0.5011   0.0648
   2.750   0.6707   0.01018   0.00225  -0.0778   0.4872   0.0683
   3.250   0.7220   0.01014   0.00246  -0.0771   0.4560   0.2112
   3.500   0.7373   0.00874   0.00272  -0.0751   0.4427   0.8017
   3.750   0.7808   0.00867   0.00294  -0.0782   0.4240   0.9948
   4.000   0.8083   0.00889   0.00308  -0.0782   0.4056   1.0000
   4.250   0.8321   0.00913   0.00323  -0.0774   0.3865   1.0000
   4.500   0.8559   0.00938   0.00340  -0.0767   0.3683   1.0000
   4.750   0.8798   0.00964   0.00358  -0.0760   0.3515   1.0000
   5.000   0.9037   0.00991   0.00378  -0.0753   0.3348   1.0000
   5.250   0.9270   0.01022   0.00400  -0.0745   0.3160   1.0000
   5.500   0.9498   0.01058   0.00425  -0.0736   0.2928   1.0000
   5.750   0.9727   0.01094   0.00452  -0.0728   0.2725   1.0000
   6.000   0.9960   0.01126   0.00477  -0.0721   0.2571   1.0000
   6.250   1.0192   0.01159   0.00505  -0.0713   0.2423   1.0000
   6.500   1.0417   0.01198   0.00535  -0.0705   0.2245   1.0000
   6.750   1.0638   0.01239   0.00567  -0.0696   0.2068   1.0000
   7.000   1.0866   0.01274   0.00597  -0.0688   0.1936   1.0000
   7.250   1.1091   0.01311   0.00630  -0.0680   0.1806   1.0000
   7.500   1.1308   0.01353   0.00665  -0.0671   0.1643   1.0000
   7.750   1.1508   0.01407   0.00706  -0.0659   0.1425   1.0000
   8.000   1.1679   0.01480   0.00760  -0.0644   0.1094   1.0000
   8.250   1.1806   0.01584   0.00838  -0.0622   0.0698   1.0000
   8.500   1.1924   0.01690   0.00923  -0.0599   0.0388   1.0000
   8.750   1.2079   0.01757   0.00986  -0.0580   0.0306   1.0000
   9.000   1.2251   0.01811   0.01043  -0.0564   0.0272   1.0000
   9.250   1.2413   0.01871   0.01105  -0.0547   0.0248   1.0000
   9.500   1.2573   0.01934   0.01172  -0.0530   0.0229   1.0000
   9.750   1.2740   0.01992   0.01234  -0.0515   0.0215   1.0000
  10.000   1.2894   0.02059   0.01305  -0.0499   0.0202   1.0000
  10.250   1.3033   0.02136   0.01386  -0.0481   0.0190   1.0000
  10.500   1.3167   0.02219   0.01474  -0.0464   0.0181   1.0000
  10.750   1.3311   0.02295   0.01557  -0.0448   0.0174   1.0000
  11.000   1.3445   0.02379   0.01647  -0.0433   0.0166   1.0000
  11.250   1.3570   0.02472   0.01746  -0.0417   0.0159   1.0000
  11.500   1.3682   0.02577   0.01855  -0.0401   0.0153   1.0000
  11.750   1.3763   0.02708   0.01991  -0.0384   0.0146   1.0000
  12.000   1.3874   0.02819   0.02110  -0.0370   0.0142   1.0000
  12.250   1.3971   0.02945   0.02244  -0.0356   0.0138   1.0000
  12.500   1.4059   0.03082   0.02389  -0.0343   0.0134   1.0000
  12.750   1.4138   0.03232   0.02548  -0.0330   0.0130   1.0000
  13.000   1.4207   0.03394   0.02718  -0.0318   0.0126   1.0000
  13.250   1.4265   0.03571   0.02902  -0.0308   0.0123   1.0000
  13.500   1.4305   0.03772   0.03110  -0.0298   0.0120   1.0000
  13.750   1.4313   0.04011   0.03357  -0.0288   0.0117   1.0000
  14.000   1.4336   0.04243   0.03598  -0.0281   0.0115   1.0000
  14.250   1.4363   0.04478   0.03844  -0.0275   0.0112   1.0000
  14.500   1.4377   0.04736   0.04113  -0.0271   0.0110   1.0000
  14.750   1.4379   0.05013   0.04400  -0.0268   0.0108   1.0000
  15.000   1.4373   0.05313   0.04710  -0.0268   0.0105   1.0000
  15.250   1.4357   0.05634   0.05042  -0.0269   0.0104   1.0000
  15.500   1.4328   0.05980   0.05399  -0.0272   0.0102   1.0000
  15.750   1.4292   0.06347   0.05776  -0.0277   0.0100   1.0000
  16.000   1.4248   0.06735   0.06175  -0.0283   0.0099   1.0000
  16.250   1.4194   0.07148   0.06598  -0.0292   0.0098   1.0000
  16.500   1.4127   0.07585   0.07046  -0.0302   0.0097   1.0000
  16.750   1.4052   0.08045   0.07515  -0.0314   0.0096   1.0000
  17.000   1.3964   0.08534   0.08015  -0.0329   0.0095   1.0000
  17.250   1.3866   0.09044   0.08536  -0.0344   0.0094   1.0000
  17.500   1.3760   0.09571   0.09074  -0.0361   0.0093   1.0000
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