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CLARK-Y 11.7% smoothed (clarkysm-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: CLARK-Y 11.7% smoothed (clarkysm-il)
Reynolds number: 50,000
Max Cl/Cd: 29.99 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkysm-il-50000.txt
Download as CSV file: xf-clarkysm-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK-Y 11.7% smoothed                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3501   0.11006   0.10325  -0.0289   1.0000   0.2480
  -8.500  -0.3261   0.10484   0.09801  -0.0270   1.0000   0.2573
  -8.250  -0.3542   0.10506   0.09842  -0.0258   1.0000   0.2641
  -8.000  -0.3350   0.10065   0.09401  -0.0238   1.0000   0.2764
  -7.750  -0.3749   0.10159   0.09519  -0.0214   1.0000   0.2809
  -7.500  -0.3551   0.09731   0.09092  -0.0192   1.0000   0.2951
  -7.250  -0.3530   0.09441   0.08809  -0.0169   1.0000   0.3045
  -7.000  -0.3875   0.09474   0.08860  -0.0130   1.0000   0.3129
  -6.750  -0.3736   0.09100   0.08489  -0.0108   1.0000   0.3240
  -6.500  -0.4246   0.09219   0.08631  -0.0058   1.0000   0.3299
  -6.250  -0.4090   0.08848   0.08262  -0.0032   1.0000   0.3433
  -5.750  -0.4398   0.08504   0.07941   0.0033   1.0000   0.3662
  -5.500  -0.4555   0.08348   0.07794   0.0064   1.0000   0.3814
  -5.000  -0.4520   0.07885   0.07341   0.0143   1.0000   0.4251
  -4.750  -0.4712   0.06046   0.05384  -0.0243   1.0000   0.2001
  -4.500  -0.4588   0.05675   0.05017  -0.0231   1.0000   0.1929
  -4.250  -0.4389   0.04907   0.04141  -0.0277   1.0000   0.1676
  -4.000  -0.4225   0.04581   0.03786  -0.0274   1.0000   0.1657
  -3.750  -0.4045   0.04280   0.03431  -0.0272   1.0000   0.1669
  -3.500  -0.3856   0.04014   0.03109  -0.0267   1.0000   0.1692
  -3.250  -0.3682   0.03839   0.02929  -0.0258   1.0000   0.1740
  -3.000  -0.3488   0.03677   0.02725  -0.0250   1.0000   0.1812
  -2.750  -0.3292   0.03517   0.02534  -0.0241   1.0000   0.1876
  -2.500  -0.3097   0.03414   0.02402  -0.0232   1.0000   0.1987
  -2.250  -0.2906   0.03310   0.02290  -0.0223   1.0000   0.2087
  -2.000  -0.2710   0.03228   0.02192  -0.0214   1.0000   0.2221
  -1.750  -0.2505   0.03159   0.02112  -0.0207   1.0000   0.2379
  -1.500  -0.2304   0.03105   0.02055  -0.0200   1.0000   0.2578
  -1.250  -0.2104   0.03060   0.02005  -0.0192   1.0000   0.2829
  -1.000  -0.1863   0.03020   0.01975  -0.0191   1.0000   0.3201
  -0.750  -0.1619   0.02968   0.01956  -0.0191   1.0000   0.3851
  -0.500  -0.0969   0.02747   0.01945  -0.0252   0.9967   1.0000
  -0.250  -0.0426   0.02910   0.02042  -0.0314   0.9824   1.0000
   0.000   0.0017   0.03030   0.02122  -0.0357   0.9676   1.0000
   0.250   0.0438   0.03141   0.02201  -0.0395   0.9524   1.0000
   0.500   0.0843   0.03245   0.02279  -0.0429   0.9369   1.0000
   0.750   0.1237   0.03342   0.02353  -0.0460   0.9210   1.0000
   1.000   0.1623   0.03432   0.02424  -0.0487   0.9045   1.0000
   1.250   0.2000   0.03516   0.02492  -0.0512   0.8880   1.0000
   1.500   0.2372   0.03594   0.02557  -0.0534   0.8713   1.0000
   1.750   0.2740   0.03666   0.02619  -0.0554   0.8546   1.0000
   2.000   0.3100   0.03734   0.02677  -0.0571   0.8381   1.0000
   2.250   0.3461   0.03795   0.02730  -0.0587   0.8215   1.0000
   2.500   0.3818   0.03850   0.02780  -0.0601   0.8050   1.0000
   2.750   0.4173   0.03898   0.02825  -0.0614   0.7886   1.0000
   3.000   0.4512   0.03945   0.02869  -0.0623   0.7725   1.0000
   3.250   0.4857   0.03982   0.02905  -0.0631   0.7564   1.0000
   3.500   0.5187   0.04018   0.02942  -0.0636   0.7405   1.0000
   3.750   0.5508   0.04051   0.02976  -0.0639   0.7247   1.0000
   4.000   0.5820   0.04082   0.03009  -0.0640   0.7091   1.0000
   4.250   0.6110   0.04119   0.03049  -0.0638   0.6937   1.0000
   4.500   0.6382   0.04162   0.03096  -0.0633   0.6785   1.0000
   4.750   0.6633   0.04216   0.03153  -0.0626   0.6636   1.0000
   5.000   0.6851   0.04290   0.03230  -0.0617   0.6490   1.0000
   5.250   0.7056   0.04374   0.03319  -0.0606   0.6349   1.0000
   5.500   0.7273   0.04457   0.03408  -0.0597   0.6219   1.0000
   5.750   0.7912   0.04289   0.03253  -0.0622   0.6138   1.0000
   6.000   0.7932   0.04484   0.03450  -0.0595   0.5996   1.0000
   6.250   0.7869   0.04761   0.03731  -0.0568   0.5858   1.0000
   6.500   0.7817   0.05065   0.04037  -0.0547   0.5730   1.0000
   6.750   0.8575   0.04766   0.03757  -0.0568   0.5666   1.0000
   7.000   0.8206   0.05307   0.04295  -0.0530   0.5527   1.0000
   7.250   0.7919   0.05842   0.04827  -0.0509   0.5409   1.0000
   7.500   0.8203   0.05903   0.04899  -0.0504   0.5320   1.0000
   7.750   0.8132   0.06269   0.05269  -0.0493   0.5218   1.0000
   8.000   0.7957   0.06734   0.05734  -0.0482   0.5122   1.0000
   8.250   0.8413   0.06636   0.05656  -0.0475   0.5019   1.0000
   8.500   0.8187   0.07142   0.06162  -0.0465   0.4910   1.0000
   8.750   0.8164   0.07453   0.06478  -0.0455   0.4788   1.0000
   9.000   0.8421   0.07454   0.06492  -0.0438   0.4622   1.0000
   9.250   1.2049   0.04164   0.03260  -0.0496   0.4082   1.0000
   9.500   1.2113   0.04245   0.03353  -0.0461   0.3875   1.0000
   9.750   1.2404   0.04182   0.03283  -0.0444   0.3583   1.0000
  10.000   1.2597   0.04200   0.03287  -0.0419   0.3282   1.0000
  10.250   1.2762   0.04262   0.03330  -0.0393   0.2989   1.0000
  10.500   1.2753   0.04427   0.03501  -0.0353   0.2781   1.0000
  10.750   1.2884   0.04561   0.03627  -0.0329   0.2581   1.0000
  11.000   1.2988   0.04713   0.03777  -0.0305   0.2420   1.0000
  11.250   1.2938   0.04938   0.04020  -0.0267   0.2313   1.0000
  11.500   1.3008   0.05136   0.04224  -0.0243   0.2205   1.0000
  11.750   1.3187   0.05302   0.04385  -0.0231   0.2091   1.0000
  12.000   1.2941   0.05616   0.04733  -0.0180   0.2054   1.0000
  12.250   1.3170   0.05773   0.04882  -0.0174   0.1950   1.0000
  12.500   1.2863   0.06159   0.05301  -0.0129   0.1933   1.0000
  12.750   1.2519   0.06630   0.05801  -0.0097   0.1923   1.0000
  13.000   1.2085   0.07250   0.06444  -0.0080   0.1927   1.0000
  13.250   1.1551   0.08107   0.07317  -0.0085   0.1943   1.0000
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