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NACA0012H for VAWT from Sandia report SAND80-2114 (naca0012h-sa) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA0012H for VAWT from Sandia report SAND80-2114 (naca0012h-sa)
Reynolds number: 50,000
Max Cl/Cd: 20.27 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca0012h-sa-50000.txt
Download as CSV file: xf-naca0012h-sa-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA0012H for VAWT from Sandia report SAND80-211
  
 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  -0.6866   0.07867   0.07048  -0.0053   1.0000   0.2535
  -8.250  -0.6936   0.07253   0.06428  -0.0070   1.0000   0.2482
  -8.000  -0.7170   0.06534   0.05697  -0.0089   1.0000   0.2437
  -7.750  -0.7364   0.05906   0.05044  -0.0094   1.0000   0.2424
  -7.500  -0.7413   0.05454   0.04568  -0.0088   1.0000   0.2448
  -7.250  -0.7436   0.05032   0.04111  -0.0078   1.0000   0.2478
  -7.000  -0.7445   0.04637   0.03665  -0.0064   1.0000   0.2511
  -6.750  -0.7257   0.04429   0.03463  -0.0053   1.0000   0.2577
  -6.500  -0.7136   0.04188   0.03197  -0.0038   1.0000   0.2645
  -6.250  -0.7032   0.03923   0.02891  -0.0023   1.0000   0.2708
  -6.000  -0.6828   0.03762   0.02737  -0.0011   1.0000   0.2793
  -5.750  -0.6693   0.03549   0.02486   0.0005   1.0000   0.2878
  -5.500  -0.6484   0.03396   0.02337   0.0017   1.0000   0.2972
  -5.250  -0.6305   0.03226   0.02150   0.0030   1.0000   0.3075
  -5.000  -0.6110   0.03079   0.01986   0.0043   1.0000   0.3189
  -4.750  -0.5895   0.02944   0.01859   0.0054   1.0000   0.3307
  -4.500  -0.5684   0.02816   0.01728   0.0066   1.0000   0.3438
  -4.250  -0.5470   0.02698   0.01607   0.0077   1.0000   0.3580
  -4.000  -0.5253   0.02594   0.01505   0.0088   1.0000   0.3741
  -3.750  -0.5030   0.02497   0.01414   0.0099   1.0000   0.3915
  -3.500  -0.4807   0.02408   0.01339   0.0111   1.0000   0.4112
  -3.250  -0.4582   0.02327   0.01272   0.0123   1.0000   0.4336
  -3.000  -0.4358   0.02250   0.01207   0.0134   1.0000   0.4603
  -2.750  -0.4132   0.02180   0.01161   0.0146   1.0000   0.4917
  -2.500  -0.3912   0.02112   0.01122   0.0161   1.0000   0.5309
  -2.250  -0.3710   0.02048   0.01098   0.0181   1.0000   0.5834
  -2.000  -0.3528   0.01992   0.01102   0.0213   1.0000   0.6589
  -1.750  -0.3335   0.01987   0.01158   0.0262   1.0000   0.7702
  -1.500  -0.2748   0.02109   0.01287   0.0259   1.0000   0.8881
  -1.250  -0.0928   0.02235   0.01366   0.0015   1.0000   0.9662
  -1.000   0.0170   0.02163   0.01273  -0.0146   1.0000   1.0000
  -0.750   0.0167   0.02127   0.01239  -0.0117   1.0000   1.0000
  -0.500   0.0138   0.02103   0.01217  -0.0083   1.0000   1.0000
  -0.250   0.0079   0.02089   0.01205  -0.0043   1.0000   1.0000
   0.000   0.0000   0.02085   0.01201   0.0000   1.0000   1.0000
   0.250  -0.0079   0.02089   0.01204   0.0043   1.0000   1.0000
   0.500  -0.0138   0.02103   0.01216   0.0083   1.0000   1.0000
   0.750  -0.0167   0.02127   0.01238   0.0117   1.0000   1.0000
   1.000  -0.0170   0.02162   0.01273   0.0146   1.0000   1.0000
   1.250   0.0928   0.02235   0.01365  -0.0015   0.9663   1.0000
   1.500   0.2746   0.02109   0.01287  -0.0259   0.8882   1.0000
   1.750   0.3335   0.01987   0.01158  -0.0262   0.7703   1.0000
   2.000   0.3527   0.01992   0.01102  -0.0213   0.6590   1.0000
   2.250   0.3710   0.02048   0.01098  -0.0181   0.5835   1.0000
   2.500   0.3911   0.02112   0.01122  -0.0160   0.5310   1.0000
   2.750   0.4131   0.02180   0.01160  -0.0146   0.4917   1.0000
   3.000   0.4357   0.02250   0.01207  -0.0134   0.4603   1.0000
   3.250   0.4581   0.02326   0.01272  -0.0122   0.4336   1.0000
   3.500   0.4806   0.02408   0.01339  -0.0111   0.4113   1.0000
   3.750   0.5030   0.02496   0.01414  -0.0099   0.3915   1.0000
   4.000   0.5252   0.02594   0.01505  -0.0088   0.3742   1.0000
   4.250   0.5469   0.02698   0.01607  -0.0077   0.3580   1.0000
   4.500   0.5683   0.02816   0.01728  -0.0066   0.3438   1.0000
   4.750   0.5894   0.02944   0.01858  -0.0054   0.3307   1.0000
   5.000   0.6109   0.03079   0.01986  -0.0043   0.3189   1.0000
   5.250   0.6304   0.03226   0.02149  -0.0030   0.3075   1.0000
   5.500   0.6484   0.03396   0.02337  -0.0017   0.2972   1.0000
   5.750   0.6693   0.03549   0.02485  -0.0005   0.2878   1.0000
   6.000   0.6828   0.03762   0.02737   0.0011   0.2793   1.0000
   6.250   0.7031   0.03923   0.02892   0.0023   0.2708   1.0000
   6.500   0.7135   0.04188   0.03197   0.0038   0.2645   1.0000
   6.750   0.7257   0.04429   0.03462   0.0053   0.2577   1.0000
   7.000   0.7446   0.04637   0.03665   0.0064   0.2511   1.0000
   7.250   0.7436   0.05032   0.04111   0.0078   0.2478   1.0000
   7.500   0.7414   0.05454   0.04568   0.0088   0.2448   1.0000
   7.750   0.7366   0.05906   0.05045   0.0094   0.2424   1.0000
   8.000   0.7173   0.06535   0.05697   0.0089   0.2437   1.0000
   8.250   0.6939   0.07255   0.06430   0.0070   0.2482   1.0000
   8.500   0.6869   0.07870   0.07051   0.0052   0.2535   1.0000
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