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CLARK YM-15 AIRFOIL (clarym15-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: CLARK YM-15 AIRFOIL (clarym15-il)
Reynolds number: 50,000
Max Cl/Cd: 12.29 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarym15-il-50000.txt
Download as CSV file: xf-clarym15-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3134   0.11547   0.10839  -0.0283   1.0000   0.2926
  -9.000  -0.2942   0.11166   0.10459  -0.0267   1.0000   0.2991
  -8.750  -0.3224   0.11190   0.10499  -0.0244   1.0000   0.3080
  -8.500  -0.3194   0.10864   0.10180  -0.0227   1.0000   0.3123
  -8.250  -0.3126   0.10619   0.09939  -0.0204   1.0000   0.3206
  -8.000  -0.3678   0.10810   0.10154  -0.0164   1.0000   0.3274
  -7.750  -0.3296   0.10277   0.09617  -0.0152   1.0000   0.3359
  -7.500  -0.3691   0.10340   0.09698  -0.0112   1.0000   0.3449
  -7.250  -0.3530   0.09973   0.09332  -0.0094   1.0000   0.3523
  -7.000  -0.3851   0.09977   0.09352  -0.0052   1.0000   0.3628
  -6.750  -0.3802   0.09677   0.09057  -0.0031   1.0000   0.3696
  -6.500  -0.4064   0.09633   0.09024   0.0012   1.0000   0.3806
  -6.250  -0.4105   0.09380   0.08779   0.0038   1.0000   0.3874
  -6.000  -0.5623   0.06799   0.06125  -0.0253   1.0000   0.1845
  -5.750  -0.5560   0.06435   0.05754  -0.0249   1.0000   0.1821
  -5.500  -0.5499   0.05990   0.05285  -0.0255   1.0000   0.1787
  -5.250  -0.5415   0.05386   0.04618  -0.0276   1.0000   0.1734
  -5.000  -0.5266   0.04894   0.04046  -0.0291   1.0000   0.1706
  -4.750  -0.5098   0.04683   0.03823  -0.0286   1.0000   0.1729
  -4.500  -0.4921   0.04506   0.03627  -0.0283   1.0000   0.1771
  -4.250  -0.4723   0.04290   0.03368  -0.0284   1.0000   0.1819
  -4.000  -0.4507   0.04073   0.03097  -0.0286   1.0000   0.1867
  -3.750  -0.4317   0.03976   0.03006  -0.0281   1.0000   0.1940
  -3.500  -0.4098   0.03842   0.02834  -0.0280   1.0000   0.2043
  -3.250  -0.3895   0.03764   0.02752  -0.0276   1.0000   0.2162
  -3.000  -0.3689   0.03691   0.02676  -0.0273   1.0000   0.2306
  -2.750  -0.3481   0.03634   0.02614  -0.0270   1.0000   0.2489
  -2.500  -0.3269   0.03589   0.02559  -0.0268   1.0000   0.2712
  -2.250  -0.3064   0.03548   0.02531  -0.0265   1.0000   0.2956
  -2.000  -0.2851   0.03517   0.02500  -0.0263   1.0000   0.3265
  -1.750  -0.2330   0.03513   0.02528  -0.0312   0.9886   0.3878
  -1.500  -0.1843   0.03504   0.02565  -0.0352   0.9769   0.4794
  -1.250  -0.1418   0.03482   0.02621  -0.0374   0.9644   0.6047
  -1.000  -0.1101   0.03447   0.02715  -0.0345   0.9514   0.8699
  -0.750  -0.0381   0.03524   0.02723  -0.0448   0.9305   1.0000
  -0.500   0.0052   0.03606   0.02762  -0.0487   0.9134   1.0000
  -0.250   0.0445   0.03684   0.02807  -0.0516   0.8976   1.0000
   0.000   0.0826   0.03760   0.02857  -0.0542   0.8824   1.0000
   0.250   0.1217   0.03834   0.02907  -0.0567   0.8675   1.0000
   0.500   0.1655   0.03904   0.02955  -0.0598   0.8532   1.0000
   0.750   0.1972   0.03964   0.02999  -0.0610   0.8378   1.0000
   1.000   0.2267   0.04024   0.03045  -0.0617   0.8217   1.0000
   1.250   0.2564   0.04085   0.03093  -0.0624   0.8056   1.0000
   1.500   0.2863   0.04144   0.03141  -0.0630   0.7894   1.0000
   1.750   0.3166   0.04201   0.03188  -0.0635   0.7731   1.0000
   2.000   0.3467   0.04256   0.03235  -0.0640   0.7570   1.0000
   2.250   0.3766   0.04310   0.03281  -0.0643   0.7412   1.0000
   2.500   0.4082   0.04356   0.03320  -0.0648   0.7259   1.0000
   2.750   0.4597   0.04325   0.03282  -0.0672   0.7148   1.0000
   3.000   0.4792   0.04405   0.03357  -0.0662   0.6987   1.0000
   3.250   0.4966   0.04503   0.03451  -0.0651   0.6830   1.0000
   3.500   0.5133   0.04611   0.03556  -0.0640   0.6681   1.0000
   3.750   0.5322   0.04719   0.03660  -0.0632   0.6547   1.0000
   4.250   0.5768   0.04914   0.03850  -0.0623   0.6320   1.0000
   4.500   0.5829   0.05121   0.04055  -0.0609   0.6198   1.0000
   4.750   0.6254   0.05088   0.04022  -0.0616   0.6123   1.0000
   5.000   0.6082   0.05481   0.04413  -0.0594   0.5998   1.0000
   5.250   0.6591   0.05391   0.04324  -0.0604   0.5940   1.0000
   5.500   0.6273   0.05910   0.04842  -0.0579   0.5818   1.0000
   5.750   0.6662   0.05917   0.04851  -0.0583   0.5754   1.0000
   6.000   0.6342   0.06462   0.05396  -0.0564   0.5661   1.0000
   6.250   0.6831   0.06398   0.05335  -0.0570   0.5597   1.0000
   6.500   0.6431   0.07016   0.05953  -0.0553   0.5519   1.0000
   6.750   0.6635   0.07181   0.06121  -0.0552   0.5450   1.0000
   7.000   0.6635   0.07504   0.06446  -0.0547   0.5384   1.0000
   7.250   0.6537   0.07901   0.06845  -0.0542   0.5327   1.0000
   7.500   0.6965   0.07907   0.06857  -0.0543   0.5241   1.0000
   7.750   0.6675   0.08456   0.07409  -0.0537   0.5197   1.0000
   8.000   0.6649   0.08813   0.07770  -0.0536   0.5147   1.0000
   8.250   0.6895   0.08964   0.07925  -0.0534   0.5051   1.0000
   8.500   0.6749   0.09422   0.08388  -0.0534   0.5019   1.0000
   8.750   0.7102   0.09488   0.08460  -0.0529   0.4892   1.0000
   9.000   0.6902   0.09995   0.08971  -0.0531   0.4864   1.0000
   9.250   0.6816   0.10437   0.09419  -0.0535   0.4845   1.0000
   9.500   0.6763   0.10863   0.09852  -0.0540   0.4834   1.0000
   9.750   0.6777   0.11338   0.10333  -0.0553   0.4876   1.0000
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