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CLARK Y AIRFOIL (clarky-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: CLARK Y AIRFOIL (clarky-il)
Reynolds number: 50,000
Max Cl/Cd: 29.62 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarky-il-50000.txt
Download as CSV file: xf-clarky-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK Y 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3410   0.10621   0.09925  -0.0263   1.0000   0.2711
  -8.250  -0.3291   0.10240   0.09548  -0.0251   1.0000   0.2802
  -8.000  -0.3587   0.10280   0.09609  -0.0238   1.0000   0.2885
  -7.750  -0.3342   0.09804   0.09130  -0.0223   1.0000   0.3003
  -7.500  -0.3487   0.09645   0.08986  -0.0203   1.0000   0.3079
  -7.250  -0.3539   0.09474   0.08824  -0.0178   1.0000   0.3191
  -7.000  -0.3507   0.09182   0.08538  -0.0156   1.0000   0.3276
  -6.750  -0.3882   0.09242   0.08620  -0.0108   1.0000   0.3366
  -6.500  -0.3717   0.08866   0.08244  -0.0090   1.0000   0.3477
  -6.250  -0.4070   0.08840   0.08239  -0.0044   1.0000   0.3557
  -6.000  -0.4206   0.08715   0.08124  -0.0011   1.0000   0.3691
  -5.750  -0.4114   0.08412   0.07824   0.0019   1.0000   0.3819
  -5.500  -0.4177   0.08215   0.07635   0.0052   1.0000   0.3970
  -5.250  -0.4281   0.08049   0.07478   0.0087   1.0000   0.4150
  -5.000  -0.4512   0.07946   0.07387   0.0119   1.0000   0.4355
  -4.750  -0.4331   0.07637   0.07079   0.0164   1.0000   0.4583
  -4.500  -0.4314   0.05863   0.05189  -0.0290   1.0000   0.2245
  -4.250  -0.4061   0.05169   0.04446  -0.0335   1.0000   0.1898
  -4.000  -0.3795   0.04648   0.03857  -0.0369   1.0000   0.1744
  -3.750  -0.3552   0.04308   0.03475  -0.0383   1.0000   0.1689
  -3.500  -0.3276   0.03982   0.03076  -0.0400   1.0000   0.1648
  -3.250  -0.3046   0.03807   0.02876  -0.0402   1.0000   0.1675
  -3.000  -0.2805   0.03649   0.02684  -0.0405   1.0000   0.1710
  -2.750  -0.2551   0.03494   0.02488  -0.0409   1.0000   0.1738
  -2.500  -0.2291   0.03365   0.02309  -0.0411   1.0000   0.1773
  -2.250  -0.2061   0.03262   0.02207  -0.0410   1.0000   0.1837
  -2.000  -0.1821   0.03190   0.02114  -0.0410   1.0000   0.1953
  -1.750  -0.1587   0.03128   0.02045  -0.0408   1.0000   0.2103
  -1.500  -0.1351   0.03065   0.01990  -0.0406   1.0000   0.2310
  -1.250  -0.1094   0.03013   0.01949  -0.0407   1.0000   0.2753
  -1.000  -0.0812   0.02923   0.01921  -0.0413   1.0000   0.3787
  -0.750  -0.0716   0.02623   0.01894  -0.0359   1.0000   1.0000
  -0.500  -0.0468   0.02692   0.01880  -0.0368   1.0000   1.0000
  -0.250  -0.0042   0.02806   0.01942  -0.0410   0.9917   1.0000
   0.000   0.0506   0.02938   0.02029  -0.0473   0.9751   1.0000
   0.250   0.1051   0.03060   0.02116  -0.0532   0.9579   1.0000
   0.500   0.1570   0.03168   0.02194  -0.0585   0.9411   1.0000
   0.750   0.1995   0.03254   0.02259  -0.0620   0.9246   1.0000
   1.000   0.2387   0.03332   0.02321  -0.0648   0.9084   1.0000
   1.250   0.2766   0.03407   0.02382  -0.0673   0.8923   1.0000
   1.500   0.3130   0.03477   0.02441  -0.0693   0.8759   1.0000
   1.750   0.3483   0.03541   0.02497  -0.0711   0.8590   1.0000
   2.000   0.3833   0.03603   0.02551  -0.0726   0.8421   1.0000
   2.250   0.4186   0.03658   0.02602  -0.0740   0.8249   1.0000
   2.500   0.4544   0.03706   0.02645  -0.0753   0.8077   1.0000
   2.750   0.4906   0.03746   0.02683  -0.0766   0.7907   1.0000
   3.000   0.5275   0.03775   0.02713  -0.0777   0.7739   1.0000
   3.250   0.5643   0.03796   0.02734  -0.0785   0.7574   1.0000
   3.500   0.6003   0.03811   0.02751  -0.0792   0.7413   1.0000
   3.750   0.6355   0.03821   0.02763  -0.0796   0.7255   1.0000
   4.000   0.6685   0.03834   0.02780  -0.0797   0.7100   1.0000
   4.250   0.6981   0.03860   0.02810  -0.0793   0.6946   1.0000
   4.500   0.7256   0.03897   0.02850  -0.0787   0.6795   1.0000
   4.750   0.7506   0.03952   0.02909  -0.0779   0.6647   1.0000
   5.000   0.7734   0.04025   0.02989  -0.0770   0.6504   1.0000
   5.250   0.7952   0.04107   0.03076  -0.0761   0.6366   1.0000
   5.500   0.8193   0.04177   0.03152  -0.0753   0.6240   1.0000
   5.750   0.8676   0.04061   0.03046  -0.0759   0.6151   1.0000
   6.000   0.8800   0.04212   0.03204  -0.0743   0.6010   1.0000
   6.250   0.8907   0.04383   0.03382  -0.0727   0.5874   1.0000
   6.500   0.9033   0.04541   0.03548  -0.0713   0.5743   1.0000
   6.750   0.9267   0.04608   0.03626  -0.0702   0.5625   1.0000
   7.000   0.9915   0.04315   0.03346  -0.0710   0.5528   1.0000
   7.250   1.0017   0.04470   0.03512  -0.0690   0.5386   1.0000
   7.500   1.0164   0.04584   0.03639  -0.0672   0.5244   1.0000
   7.750   1.0478   0.04535   0.03601  -0.0660   0.5094   1.0000
   8.000   1.1029   0.04267   0.03340  -0.0657   0.4921   1.0000
   8.250   1.1433   0.04141   0.03218  -0.0650   0.4741   1.0000
   8.500   1.1591   0.04217   0.03306  -0.0628   0.4566   1.0000
   8.750   1.1777   0.04275   0.03375  -0.0609   0.4383   1.0000
   9.000   1.2049   0.04271   0.03379  -0.0594   0.4185   1.0000
   9.250   1.2442   0.04201   0.03301  -0.0589   0.3967   1.0000
   9.500   1.2528   0.04349   0.03464  -0.0562   0.3771   1.0000
   9.750   1.2746   0.04420   0.03538  -0.0545   0.3559   1.0000
  10.000   1.3042   0.04488   0.03594  -0.0538   0.3353   1.0000
  10.250   1.3144   0.04680   0.03799  -0.0515   0.3190   1.0000
  10.500   1.3280   0.04857   0.03985  -0.0496   0.3038   1.0000
  10.750   1.3409   0.05037   0.04176  -0.0477   0.2902   1.0000
  11.000   1.3177   0.05428   0.04606  -0.0431   0.2829   1.0000
  11.250   1.3370   0.05612   0.04800  -0.0420   0.2723   1.0000
  11.500   1.2972   0.06109   0.05330  -0.0370   0.2691   1.0000
  11.750   1.2377   0.06803   0.06039  -0.0328   0.2687   1.0000
  12.000   1.1120   0.08579   0.07807  -0.0355   0.2728   1.0000
  12.250   1.3618   0.06228   0.05459  -0.0327   0.2297   1.0000
  12.500   1.3213   0.06787   0.06046  -0.0287   0.2300   1.0000
  12.750   1.3277   0.06776   0.06037  -0.0262   0.2160   1.0000
  13.000   1.3716   0.06211   0.05435  -0.0240   0.1874   1.0000
  13.250   1.3285   0.06839   0.06104  -0.0213   0.1888   1.0000
  13.500   1.2920   0.07486   0.06775  -0.0204   0.1885   1.0000
  13.750   1.2584   0.08181   0.07483  -0.0208   0.1874   1.0000
  14.500   1.2881   0.08254   0.07524  -0.0147   0.1321   1.0000
  14.750   1.2556   0.08980   0.08275  -0.0162   0.1318   1.0000
  15.000   0.8641   0.18509   0.17714  -0.0828   0.3321   1.0000
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