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ARA-D 10% AIRFOIL (arad10-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: ARA-D 10% AIRFOIL (arad10-il)
Reynolds number: 50,000
Max Cl/Cd: 34.72 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-arad10-il-50000.txt
Download as CSV file: xf-arad10-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ARA-D 10% 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3525   0.10890   0.10186  -0.0159   1.0000   0.1855
  -8.000  -0.3652   0.10793   0.10102  -0.0175   1.0000   0.1912
  -7.750  -0.3851   0.10719   0.10046  -0.0204   1.0000   0.1931
  -7.500  -0.3493   0.10054   0.09374  -0.0162   1.0000   0.2030
  -7.250  -0.3688   0.09998   0.09335  -0.0186   1.0000   0.2087
  -7.000  -0.3565   0.09540   0.08883  -0.0164   1.0000   0.2141
  -6.750  -0.3557   0.09297   0.08649  -0.0162   1.0000   0.2229
  -6.500  -0.3634   0.09059   0.08423  -0.0181   1.0000   0.2286
  -6.250  -0.3533   0.08721   0.08091  -0.0151   1.0000   0.2368
  -6.000  -0.3605   0.08503   0.07882  -0.0176   1.0000   0.2455
  -5.750  -0.3530   0.08195   0.07581  -0.0145   1.0000   0.2547
  -5.500  -0.3533   0.07920   0.07314  -0.0146   1.0000   0.2648
  -5.250  -0.3526   0.07682   0.07082  -0.0154   1.0000   0.2795
  -5.000  -0.3493   0.07429   0.06833  -0.0144   1.0000   0.2963
  -4.750  -0.3456   0.07161   0.06573  -0.0120   1.0000   0.3143
  -4.500  -0.3419   0.06901   0.06321  -0.0089   1.0000   0.3338
  -4.250  -0.3380   0.06678   0.06105  -0.0067   1.0000   0.3595
  -4.000  -0.3355   0.06424   0.05861  -0.0033   1.0000   0.3868
  -3.750  -0.3345   0.06207   0.05653   0.0013   1.0000   0.4227
  -3.500  -0.3379   0.06014   0.05473   0.0079   1.0000   0.4722
  -3.250  -0.1899   0.04809   0.04069  -0.0429   1.0000   0.2270
  -2.750  -0.1267   0.04059   0.03235  -0.0482   1.0000   0.1969
  -2.500  -0.0977   0.03836   0.02976  -0.0497   1.0000   0.1986
  -2.250  -0.0686   0.03669   0.02770  -0.0509   1.0000   0.2050
  -2.000  -0.0394   0.03519   0.02579  -0.0521   1.0000   0.2124
  -1.750  -0.0135   0.03420   0.02459  -0.0527   1.0000   0.2219
  -1.500   0.0120   0.03334   0.02356  -0.0532   1.0000   0.2334
  -1.250   0.0376   0.03277   0.02271  -0.0538   1.0000   0.2461
  -1.000   0.0621   0.03243   0.02220  -0.0542   1.0000   0.2610
  -0.750   0.0854   0.03216   0.02189  -0.0544   1.0000   0.2786
  -0.500   0.1086   0.03206   0.02177  -0.0546   1.0000   0.2987
  -0.250   0.1325   0.03213   0.02182  -0.0550   1.0000   0.3237
   0.000   0.1753   0.03200   0.02181  -0.0586   0.9944   0.3679
   0.250   0.2382   0.03095   0.02172  -0.0654   0.9831   0.5041
   0.500   0.2823   0.02999   0.02128  -0.0679   0.9627   1.0000
   0.750   0.3436   0.03059   0.02141  -0.0744   0.9428   1.0000
   1.000   0.4008   0.03093   0.02148  -0.0798   0.9218   1.0000
   1.250   0.4483   0.03112   0.02152  -0.0833   0.8990   1.0000
   1.500   0.5039   0.03098   0.02125  -0.0876   0.8778   1.0000
   1.750   0.5659   0.03037   0.02056  -0.0924   0.8580   1.0000
   2.000   0.6057   0.03012   0.02027  -0.0933   0.8341   1.0000
   2.250   0.6521   0.02939   0.01951  -0.0945   0.8118   1.0000
   2.500   0.6987   0.02837   0.01845  -0.0950   0.7905   1.0000
   2.750   0.7293   0.02797   0.01804  -0.0935   0.7632   1.0000
   3.000   0.7677   0.02698   0.01697  -0.0922   0.7392   1.0000
   3.250   0.7953   0.02659   0.01652  -0.0898   0.7080   1.0000
   3.500   0.8229   0.02623   0.01606  -0.0874   0.6752   1.0000
   3.750   0.8497   0.02598   0.01564  -0.0850   0.6403   1.0000
   4.000   0.8759   0.02594   0.01538  -0.0827   0.6043   1.0000
   4.250   0.8998   0.02631   0.01555  -0.0807   0.5667   1.0000
   4.500   0.9243   0.02679   0.01581  -0.0789   0.5323   1.0000
   4.750   0.9499   0.02736   0.01610  -0.0776   0.5029   1.0000
   5.000   0.9737   0.02822   0.01688  -0.0764   0.4747   1.0000
   5.250   0.9993   0.02905   0.01749  -0.0755   0.4519   1.0000
   5.500   1.0231   0.03013   0.01854  -0.0747   0.4304   1.0000
   5.750   1.0477   0.03120   0.01957  -0.0740   0.4118   1.0000
   6.000   1.0721   0.03237   0.02070  -0.0733   0.3953   1.0000
   6.250   1.0964   0.03362   0.02193  -0.0727   0.3805   1.0000
   6.500   1.1210   0.03489   0.02318  -0.0721   0.3670   1.0000
   6.750   1.1465   0.03615   0.02436  -0.0716   0.3547   1.0000
   7.000   1.1664   0.03787   0.02632  -0.0708   0.3426   1.0000
   7.250   1.1876   0.03961   0.02817  -0.0700   0.3319   1.0000
   7.500   1.2133   0.04103   0.02952  -0.0696   0.3222   1.0000
   7.750   1.2270   0.04344   0.03233  -0.0683   0.3128   1.0000
   8.000   1.2517   0.04503   0.03384  -0.0679   0.3041   1.0000
   8.250   1.2598   0.04796   0.03727  -0.0662   0.2963   1.0000
   8.500   1.2881   0.04949   0.03862  -0.0661   0.2887   1.0000
   8.750   1.2831   0.05351   0.04329  -0.0636   0.2826   1.0000
   9.000   1.2988   0.05582   0.04571  -0.0625   0.2756   1.0000
   9.250   1.3075   0.05915   0.04923  -0.0611   0.2705   1.0000
   9.500   1.2821   0.06506   0.05566  -0.0581   0.2677   1.0000
   9.750   1.2378   0.07264   0.06362  -0.0551   0.2670   1.0000
  10.000   1.1623   0.08347   0.07465  -0.0531   0.2699   1.0000
  10.250   1.1000   0.09701   0.08824  -0.0572   0.2728   1.0000
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