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


Details Polar file
Airfoil: CLARK K AIRFOIL (clarkk-il)
Reynolds number: 50,000
Max Cl/Cd: 32.18 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkk-il-50000.txt
Download as CSV file: xf-clarkk-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3670   0.12687   0.11916  -0.0249   1.0000   0.2386
 -10.250  -0.3559   0.12345   0.11575  -0.0247   1.0000   0.2465
 -10.000  -0.3858   0.12517   0.11762  -0.0266   1.0000   0.2522
  -9.750  -0.3481   0.11753   0.10989  -0.0252   1.0000   0.2592
  -9.500  -0.3609   0.11696   0.10942  -0.0258   1.0000   0.2683
  -9.250  -0.3427   0.11208   0.10454  -0.0251   1.0000   0.2750
  -9.000  -0.3520   0.11103   0.10358  -0.0251   1.0000   0.2850
  -8.750  -0.3400   0.10689   0.09947  -0.0246   1.0000   0.2910
  -8.500  -0.3420   0.10503   0.09768  -0.0239   1.0000   0.3010
  -8.250  -0.3409   0.10205   0.09478  -0.0232   1.0000   0.3072
  -8.000  -0.3404   0.09997   0.09277  -0.0218   1.0000   0.3177
  -7.750  -0.3384   0.09711   0.08998  -0.0205   1.0000   0.3255
  -7.500  -0.3603   0.09691   0.08994  -0.0180   1.0000   0.3368
  -7.250  -0.3388   0.09274   0.08576  -0.0167   1.0000   0.3478
  -7.000  -0.3695   0.09250   0.08572  -0.0130   1.0000   0.3565
  -6.750  -0.3667   0.09032   0.08360  -0.0103   1.0000   0.3699
  -6.500  -0.3596   0.08734   0.08066  -0.0081   1.0000   0.3796
  -6.250  -0.4217   0.08942   0.08303  -0.0014   1.0000   0.3892
  -6.000  -0.3931   0.08519   0.07877   0.0004   1.0000   0.4031
  -5.750  -0.3935   0.08287   0.07652   0.0035   1.0000   0.4150
  -5.500  -0.4060   0.08131   0.07507   0.0073   1.0000   0.4293
  -5.250  -0.4145   0.07961   0.07345   0.0110   1.0000   0.4459
  -5.000  -0.4161   0.07770   0.07161   0.0146   1.0000   0.4655
  -4.750  -0.4435   0.07731   0.07134   0.0195   1.0000   0.4918
  -4.500  -0.4175   0.07406   0.06810   0.0230   1.0000   0.5185
  -4.250  -0.4145   0.05292   0.04529  -0.0320   1.0000   0.2188
  -4.000  -0.3918   0.04846   0.04047  -0.0342   1.0000   0.2036
  -3.750  -0.3688   0.04540   0.03712  -0.0355   1.0000   0.1948
  -3.500  -0.3390   0.04164   0.03249  -0.0383   1.0000   0.1837
  -3.250  -0.3158   0.03957   0.03017  -0.0388   1.0000   0.1811
  -3.000  -0.2917   0.03782   0.02808  -0.0394   1.0000   0.1804
  -2.750  -0.2676   0.03641   0.02634  -0.0398   1.0000   0.1809
  -2.500  -0.2436   0.03519   0.02482  -0.0400   1.0000   0.1811
  -2.250  -0.2196   0.03414   0.02349  -0.0402   1.0000   0.1809
  -2.000  -0.1959   0.03332   0.02242  -0.0402   1.0000   0.1813
  -1.750  -0.1726   0.03270   0.02158  -0.0402   1.0000   0.1825
  -1.500  -0.1497   0.03227   0.02093  -0.0400   1.0000   0.1845
  -1.250  -0.1282   0.03193   0.02063  -0.0399   1.0000   0.1887
  -1.000  -0.1069   0.03183   0.02051  -0.0396   1.0000   0.1948
  -0.750  -0.0847   0.03186   0.02038  -0.0394   1.0000   0.2012
  -0.500  -0.0620   0.03186   0.02046  -0.0395   1.0000   0.2085
  -0.250  -0.0116   0.03217   0.02081  -0.0443   0.9903   0.2267
   0.000   0.0400   0.03216   0.02120  -0.0495   0.9799   0.2812
   0.500   0.1189   0.03117   0.02221  -0.0539   0.9566   1.0000
   0.750   0.1563   0.03214   0.02290  -0.0567   0.9432   1.0000
   1.000   0.1924   0.03311   0.02364  -0.0592   0.9295   1.0000
   1.250   0.2282   0.03407   0.02441  -0.0616   0.9158   1.0000
   1.500   0.2643   0.03502   0.02520  -0.0640   0.9019   1.0000
   1.750   0.3013   0.03594   0.02598  -0.0663   0.8877   1.0000
   2.000   0.3395   0.03681   0.02674  -0.0688   0.8736   1.0000
   2.250   0.3801   0.03760   0.02743  -0.0714   0.8592   1.0000
   2.500   0.4132   0.03832   0.02809  -0.0727   0.8438   1.0000
   2.750   0.4452   0.03900   0.02873  -0.0737   0.8279   1.0000
   3.000   0.4783   0.03961   0.02930  -0.0747   0.8118   1.0000
   3.250   0.5123   0.04012   0.02980  -0.0756   0.7954   1.0000
   3.500   0.5470   0.04051   0.03019  -0.0764   0.7789   1.0000
   3.750   0.5819   0.04079   0.03049  -0.0770   0.7624   1.0000
   4.000   0.6165   0.04098   0.03072  -0.0774   0.7459   1.0000
   4.250   0.6517   0.04102   0.03080  -0.0776   0.7294   1.0000
   4.500   0.6868   0.04095   0.03080  -0.0776   0.7131   1.0000
   4.750   0.7219   0.04076   0.03068  -0.0774   0.6968   1.0000
   5.000   0.7572   0.04040   0.03040  -0.0770   0.6806   1.0000
   5.250   0.7913   0.04003   0.03012  -0.0763   0.6643   1.0000
   5.500   0.8270   0.03945   0.02963  -0.0756   0.6480   1.0000
   5.750   0.8630   0.03881   0.02910  -0.0748   0.6316   1.0000
   6.000   0.8996   0.03812   0.02849  -0.0741   0.6150   1.0000
   6.250   0.9207   0.03853   0.02899  -0.0723   0.5958   1.0000
   6.500   0.9463   0.03872   0.02927  -0.0709   0.5776   1.0000
   6.750   0.9754   0.03870   0.02934  -0.0697   0.5600   1.0000
   7.000   1.0041   0.03880   0.02952  -0.0686   0.5430   1.0000
   7.250   1.0315   0.03908   0.02991  -0.0676   0.5264   1.0000
   7.500   1.0573   0.03954   0.03046  -0.0664   0.5102   1.0000
   7.750   1.0815   0.04023   0.03124  -0.0653   0.4949   1.0000
   8.000   1.1059   0.04091   0.03204  -0.0641   0.4799   1.0000
   8.250   1.1319   0.04155   0.03277  -0.0631   0.4654   1.0000
   8.500   1.1583   0.04209   0.03340  -0.0621   0.4505   1.0000
   8.750   1.1825   0.04269   0.03412  -0.0608   0.4348   1.0000
   9.000   1.1996   0.04335   0.03491  -0.0586   0.4168   1.0000
   9.250   1.2383   0.04074   0.03209  -0.0568   0.3856   1.0000
   9.500   1.2618   0.03926   0.03041  -0.0542   0.3550   1.0000
   9.750   1.2693   0.03983   0.03109  -0.0509   0.3323   1.0000
  10.000   1.2834   0.03988   0.03103  -0.0481   0.3057   1.0000
  10.250   1.2877   0.04034   0.03136  -0.0442   0.2753   1.0000
  10.500   1.2810   0.04157   0.03247  -0.0393   0.2422   1.0000
  10.750   1.2702   0.04334   0.03402  -0.0342   0.2098   1.0000
  11.000   1.2655   0.04532   0.03568  -0.0301   0.1832   1.0000
  11.250   1.2628   0.04775   0.03815  -0.0268   0.1649   1.0000
  11.500   1.2666   0.05005   0.04042  -0.0244   0.1508   1.0000
  11.750   1.2765   0.05232   0.04261  -0.0227   0.1394   1.0000
  12.000   1.2849   0.05491   0.04534  -0.0209   0.1313   1.0000
  12.250   1.2924   0.05794   0.04851  -0.0194   0.1251   1.0000
  12.500   1.2904   0.06108   0.05191  -0.0174   0.1206   1.0000
  12.750   0.8713   0.10054   0.09351  -0.0206   0.2027   1.0000
  13.000   0.8264   0.11250   0.10541  -0.0247   0.2009   1.0000
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