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CLARK YM-15 AIRFOIL (clarym15-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: CLARK YM-15 AIRFOIL (clarym15-il)
Reynolds number: 50,000
Max Cl/Cd: 31.01 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarym15-il-50000-n5.txt
Download as CSV file: xf-clarym15-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK YM-15 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3666   0.10299   0.09535  -0.0496   1.0000   0.0853
 -10.000  -0.3768   0.09915   0.09160  -0.0499   1.0000   0.0847
  -9.750  -0.3911   0.09516   0.08771  -0.0501   1.0000   0.0842
  -9.500  -0.4097   0.09100   0.08367  -0.0502   1.0000   0.0837
  -9.250  -0.4360   0.08641   0.07919  -0.0502   1.0000   0.0831
  -9.000  -0.4832   0.08001   0.07290  -0.0513   1.0000   0.0820
  -8.750  -0.5421   0.07411   0.06703  -0.0498   1.0000   0.0808
  -8.500  -0.5852   0.06870   0.06149  -0.0480   1.0000   0.0802
  -8.250  -0.6102   0.06445   0.05705  -0.0460   1.0000   0.0801
  -8.000  -0.6084   0.06057   0.05294  -0.0470   0.9959   0.0810
  -7.750  -0.5940   0.05658   0.04862  -0.0496   0.9886   0.0827
  -7.500  -0.5774   0.05246   0.04403  -0.0523   0.9818   0.0847
  -7.250  -0.5615   0.04865   0.03969  -0.0537   0.9742   0.0865
  -7.000  -0.5394   0.04514   0.03555  -0.0555   0.9679   0.0882
  -6.750  -0.5162   0.04266   0.03267  -0.0563   0.9609   0.0899
  -6.500  -0.4845   0.04114   0.03105  -0.0582   0.9558   0.0926
  -6.250  -0.4611   0.03972   0.02942  -0.0584   0.9480   0.0962
  -6.000  -0.4300   0.03794   0.02715  -0.0599   0.9424   0.1008
  -5.750  -0.4030   0.03668   0.02584  -0.0605   0.9357   0.1044
  -5.500  -0.3736   0.03559   0.02463  -0.0613   0.9290   0.1092
  -5.250  -0.3378   0.03441   0.02321  -0.0632   0.9244   0.1168
  -5.000  -0.3155   0.03369   0.02250  -0.0627   0.9158   0.1235
  -4.750  -0.2819   0.03282   0.02156  -0.0641   0.9102   0.1337
  -4.500  -0.2538   0.03218   0.02082  -0.0644   0.9033   0.1456
  -4.000  -0.1883   0.03109   0.01979  -0.0669   0.8913   0.1790
  -3.750  -0.1670   0.03076   0.01950  -0.0661   0.8822   0.1965
  -3.500  -0.1322   0.03027   0.01904  -0.0676   0.8765   0.2222
  -3.250  -0.1048   0.02990   0.01874  -0.0678   0.8691   0.2488
  -3.000  -0.0759   0.02952   0.01840  -0.0681   0.8619   0.2815
  -2.750  -0.0388   0.02900   0.01801  -0.0699   0.8573   0.3225
  -2.500  -0.0208   0.02884   0.01796  -0.0684   0.8473   0.3566
  -2.250   0.0131   0.02838   0.01770  -0.0695   0.8419   0.4059
  -2.000   0.0341   0.02816   0.01772  -0.0684   0.8330   0.4559
  -1.750   0.0620   0.02773   0.01765  -0.0680   0.8264   0.5309
  -1.500   0.0872   0.02729   0.01773  -0.0665   0.8200   0.6371
  -1.250   0.1102   0.02717   0.01806  -0.0640   0.8113   0.7644
  -1.000   0.1761   0.02696   0.01788  -0.0689   0.8068   0.8958
  -0.750   0.2404   0.02687   0.01758  -0.0751   0.7960   0.9650
  -0.500   0.3235   0.02619   0.01659  -0.0847   0.7890   1.0000
  -0.250   0.3375   0.02617   0.01640  -0.0824   0.7751   1.0000
   0.000   0.3569   0.02613   0.01619  -0.0808   0.7635   1.0000
   0.250   0.3858   0.02594   0.01582  -0.0807   0.7549   1.0000
   0.500   0.3997   0.02614   0.01590  -0.0784   0.7425   1.0000
   0.750   0.4312   0.02591   0.01551  -0.0785   0.7346   1.0000
   1.000   0.4472   0.02609   0.01559  -0.0764   0.7222   1.0000
   1.250   0.4665   0.02622   0.01561  -0.0748   0.7107   1.0000
   1.500   0.4980   0.02600   0.01527  -0.0748   0.7022   1.0000
   1.750   0.5140   0.02625   0.01544  -0.0727   0.6891   1.0000
   2.000   0.5369   0.02631   0.01541  -0.0716   0.6777   1.0000
   2.250   0.5669   0.02614   0.01514  -0.0713   0.6679   1.0000
   2.500   0.5847   0.02638   0.01533  -0.0695   0.6544   1.0000
   2.750   0.6071   0.02650   0.01538  -0.0683   0.6419   1.0000
   3.000   0.6382   0.02631   0.01509  -0.0682   0.6317   1.0000
   3.250   0.6583   0.02653   0.01526  -0.0667   0.6179   1.0000
   3.500   0.6788   0.02676   0.01546  -0.0653   0.6043   1.0000
   3.750   0.7025   0.02691   0.01555  -0.0643   0.5913   1.0000
   4.000   0.7309   0.02689   0.01544  -0.0639   0.5796   1.0000
   4.250   0.7535   0.02713   0.01564  -0.0628   0.5662   1.0000
   4.500   0.7739   0.02750   0.01598  -0.0615   0.5526   1.0000
   4.750   0.7974   0.02780   0.01622  -0.0606   0.5403   1.0000
   5.000   0.8271   0.02787   0.01620  -0.0605   0.5297   1.0000
   5.250   0.8448   0.02846   0.01679  -0.0590   0.5166   1.0000
   5.500   0.8664   0.02894   0.01726  -0.0580   0.5053   1.0000
   5.750   0.8951   0.02917   0.01742  -0.0579   0.4960   1.0000
   6.000   0.9114   0.02993   0.01822  -0.0563   0.4848   1.0000
   6.250   0.9374   0.03032   0.01857  -0.0559   0.4759   1.0000
   6.500   0.9561   0.03101   0.01931  -0.0547   0.4660   1.0000
   6.750   0.9790   0.03157   0.01987  -0.0540   0.4576   1.0000
   7.000   0.9988   0.03225   0.02059  -0.0530   0.4488   1.0000
   7.250   1.0200   0.03289   0.02126  -0.0521   0.4406   1.0000
   7.500   1.0391   0.03360   0.02201  -0.0510   0.4320   1.0000
   7.750   1.0591   0.03428   0.02273  -0.0500   0.4239   1.0000
   8.000   1.0770   0.03501   0.02350  -0.0487   0.4153   1.0000
   8.250   1.0951   0.03575   0.02430  -0.0475   0.4071   1.0000
   8.500   1.1124   0.03648   0.02508  -0.0461   0.3984   1.0000
   8.750   1.1277   0.03731   0.02596  -0.0446   0.3900   1.0000
   9.000   1.1447   0.03798   0.02667  -0.0432   0.3811   1.0000
   9.250   1.1547   0.03896   0.02774  -0.0410   0.3724   1.0000
   9.500   1.1740   0.03948   0.02827  -0.0398   0.3633   1.0000
   9.750   1.1774   0.04080   0.02970  -0.0371   0.3544   1.0000
  10.000   1.2009   0.04112   0.02998  -0.0364   0.3451   1.0000
  10.250   1.1966   0.04291   0.03197  -0.0333   0.3364   1.0000
  10.500   1.2228   0.04308   0.03207  -0.0327   0.3273   1.0000
  10.750   1.2109   0.04542   0.03465  -0.0294   0.3187   1.0000
  11.000   1.2372   0.04553   0.03469  -0.0288   0.3098   1.0000
  11.250   1.2189   0.04851   0.03793  -0.0256   0.3014   1.0000
  11.500   1.2432   0.04865   0.03804  -0.0248   0.2926   1.0000
  11.750   1.2186   0.05244   0.04210  -0.0221   0.2842   1.0000
  12.000   1.2415   0.05252   0.04215  -0.0212   0.2756   1.0000
  12.250   1.2081   0.05761   0.04753  -0.0191   0.2673   1.0000
  12.500   1.2323   0.05744   0.04732  -0.0181   0.2592   1.0000
  12.750   1.1871   0.06452   0.05470  -0.0173   0.2507   1.0000
  13.000   1.2136   0.06388   0.05400  -0.0162   0.2431   1.0000
  13.250   1.1525   0.07401   0.06443  -0.0172   0.2341   1.0000
  13.500   1.1874   0.07203   0.06240  -0.0156   0.2277   1.0000
  13.750   1.1065   0.08648   0.07712  -0.0194   0.2175   1.0000
  14.000   1.1558   0.08195   0.07256  -0.0166   0.2133   1.0000
  14.250   1.0632   0.10021   0.09099  -0.0231   0.2016   1.0000
  14.500   1.1096   0.09541   0.08622  -0.0200   0.1989   1.0000
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