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SA7026 (sa7026-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: SA7026 (sa7026-il)
Reynolds number: 100,000
Max Cl/Cd: 61.89 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7026-il-100000-n5.txt
Download as CSV file: xf-sa7026-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7026                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2769   0.09930   0.09499  -0.0343   1.0000   0.0476
  -8.750  -0.2812   0.09707   0.09281  -0.0330   1.0000   0.0482
  -8.500  -0.2867   0.09485   0.09064  -0.0316   1.0000   0.0488
  -8.250  -0.2845   0.09142   0.08724  -0.0326   0.9980   0.0497
  -8.000  -0.2766   0.08712   0.08295  -0.0356   0.9945   0.0504
  -7.750  -0.2703   0.08288   0.07872  -0.0384   0.9903   0.0510
  -7.500  -0.2632   0.07847   0.07432  -0.0416   0.9859   0.0512
  -7.250  -0.2567   0.07396   0.06982  -0.0450   0.9814   0.0510
  -7.000  -0.2534   0.06964   0.06552  -0.0480   0.9751   0.0501
  -6.500  -0.3160   0.07148   0.06706  -0.0581   0.9733   0.0311
  -6.250  -0.2983   0.06706   0.06260  -0.0621   0.9685   0.0290
  -6.000  -0.2797   0.06161   0.05706  -0.0682   0.9613   0.0271
  -5.750  -0.2504   0.05373   0.04894  -0.0777   0.9566   0.0246
  -5.250  -0.1980   0.04150   0.03575  -0.0870   0.9444   0.0215
  -5.000  -0.1757   0.03761   0.03146  -0.0888   0.9386   0.0212
  -4.750  -0.1476   0.03436   0.02765  -0.0906   0.9336   0.0216
  -4.500  -0.1171   0.03078   0.02363  -0.0932   0.9305   0.0233
  -4.250  -0.0921   0.02883   0.02130  -0.0935   0.9250   0.0244
  -4.000  -0.0624   0.02658   0.01857  -0.0941   0.9204   0.0246
  -3.750  -0.0282   0.02459   0.01616  -0.0953   0.9175   0.0247
  -3.500   0.0019   0.02311   0.01439  -0.0957   0.9133   0.0251
  -3.250   0.0286   0.02193   0.01301  -0.0953   0.9075   0.0257
  -3.000   0.0614   0.02083   0.01175  -0.0961   0.9039   0.0266
  -2.750   0.0897   0.02000   0.01075  -0.0961   0.8987   0.0280
  -2.500   0.1174   0.01936   0.00994  -0.0960   0.8928   0.0300
  -2.250   0.1509   0.01865   0.00908  -0.0969   0.8892   0.0342
  -2.000   0.1755   0.01808   0.00856  -0.0962   0.8822   0.0552
  -1.750   0.2033   0.01661   0.00828  -0.0970   0.8775   0.3151
  -1.500   0.2316   0.01557   0.00817  -0.0969   0.8741   0.5874
  -1.250   0.2488   0.01492   0.00819  -0.0936   0.8664   0.8222
  -1.000   0.3032   0.01462   0.00773  -0.0985   0.8636   1.0000
  -0.750   0.3314   0.01464   0.00752  -0.0985   0.8570   1.0000
  -0.500   0.3598   0.01464   0.00731  -0.0985   0.8501   1.0000
  -0.250   0.3877   0.01465   0.00714  -0.0984   0.8431   1.0000
   0.000   0.4162   0.01464   0.00698  -0.0983   0.8361   1.0000
   0.250   0.4430   0.01467   0.00688  -0.0980   0.8285   1.0000
   0.500   0.4723   0.01463   0.00673  -0.0980   0.8217   1.0000
   0.750   0.4979   0.01469   0.00670  -0.0975   0.8130   1.0000
   1.000   0.5285   0.01460   0.00653  -0.0977   0.8066   1.0000
   1.250   0.5530   0.01467   0.00655  -0.0970   0.7966   1.0000
   1.500   0.5804   0.01466   0.00648  -0.0966   0.7877   1.0000
   1.750   0.6097   0.01458   0.00634  -0.0966   0.7792   1.0000
   2.000   0.6349   0.01462   0.00636  -0.0959   0.7681   1.0000
   2.250   0.6613   0.01464   0.00639  -0.0954   0.7573   1.0000
   2.500   0.6887   0.01463   0.00636  -0.0950   0.7468   1.0000
   2.750   0.7167   0.01461   0.00632  -0.0947   0.7360   1.0000
   3.000   0.7440   0.01461   0.00632  -0.0943   0.7239   1.0000
   3.250   0.7703   0.01465   0.00641  -0.0938   0.7102   1.0000
   3.500   0.7962   0.01471   0.00647  -0.0932   0.6953   1.0000
   3.750   0.8215   0.01480   0.00658  -0.0925   0.6786   1.0000
   4.000   0.8472   0.01488   0.00668  -0.0918   0.6614   1.0000
   4.250   0.8733   0.01498   0.00678  -0.0912   0.6438   1.0000
   4.500   0.8988   0.01512   0.00698  -0.0905   0.6252   1.0000
   4.750   0.9235   0.01530   0.00718  -0.0897   0.6046   1.0000
   5.000   0.9479   0.01552   0.00740  -0.0889   0.5829   1.0000
   5.250   0.9717   0.01577   0.00764  -0.0879   0.5592   1.0000
   5.500   0.9946   0.01608   0.00799  -0.0869   0.5334   1.0000
   5.750   1.0169   0.01643   0.00833  -0.0858   0.5066   1.0000
   6.000   1.0385   0.01684   0.00873  -0.0846   0.4796   1.0000
   6.250   1.0593   0.01730   0.00918  -0.0833   0.4521   1.0000
   6.500   1.0793   0.01782   0.00967  -0.0819   0.4236   1.0000
   6.750   1.0980   0.01840   0.01021  -0.0803   0.3933   1.0000
   7.000   1.1156   0.01904   0.01087  -0.0787   0.3608   1.0000
   7.250   1.1322   0.01974   0.01153  -0.0769   0.3278   1.0000
   7.500   1.1478   0.02051   0.01224  -0.0750   0.2963   1.0000
   7.750   1.1622   0.02135   0.01303  -0.0731   0.2615   1.0000
   8.000   1.1716   0.02248   0.01391  -0.0706   0.2133   1.0000
   8.250   1.1784   0.02388   0.01492  -0.0679   0.1554   1.0000
   8.500   1.1834   0.02544   0.01608  -0.0651   0.1026   1.0000
   8.750   1.1875   0.02714   0.01743  -0.0623   0.0596   1.0000
   9.000   1.1928   0.02881   0.01903  -0.0595   0.0366   1.0000
   9.250   1.1964   0.03065   0.02084  -0.0566   0.0254   1.0000
   9.500   1.2023   0.03230   0.02265  -0.0540   0.0214   1.0000
   9.750   1.2068   0.03405   0.02456  -0.0515   0.0190   1.0000
  10.000   1.2087   0.03603   0.02669  -0.0490   0.0176   1.0000
  10.250   1.2075   0.03834   0.02915  -0.0464   0.0166   1.0000
  10.500   1.2101   0.04040   0.03142  -0.0444   0.0161   1.0000
  10.750   1.2124   0.04261   0.03384  -0.0424   0.0155   1.0000
  11.000   1.2154   0.04487   0.03630  -0.0408   0.0148   1.0000
  11.250   1.2185   0.04722   0.03883  -0.0393   0.0137   1.0000
  11.500   1.2214   0.04965   0.04144  -0.0381   0.0130   1.0000
  11.750   1.2232   0.05224   0.04419  -0.0370   0.0122   1.0000
  12.000   1.2240   0.05503   0.04715  -0.0362   0.0117   1.0000
  12.250   1.2235   0.05812   0.05040  -0.0354   0.0113   1.0000
  12.500   1.2229   0.06139   0.05393  -0.0348   0.0111   1.0000
  12.750   1.2211   0.06498   0.05772  -0.0344   0.0110   1.0000
  13.000   1.2174   0.06896   0.06192  -0.0342   0.0108   1.0000
  13.250   1.2119   0.07326   0.06646  -0.0344   0.0107   1.0000
  13.500   1.2045   0.07792   0.07136  -0.0351   0.0107   1.0000
  13.750   1.1943   0.08310   0.07679  -0.0363   0.0106   1.0000
  14.000   1.1841   0.08842   0.08235  -0.0380   0.0106   1.0000
  14.250   1.1715   0.09444   0.08861  -0.0404   0.0106   1.0000
  14.500   1.1594   0.10062   0.09502  -0.0433   0.0106   1.0000
  14.750   1.1463   0.10737   0.10198  -0.0469   0.0106   1.0000
  15.000   1.1325   0.11470   0.10952  -0.0512   0.0107   1.0000
  15.250   1.1188   0.12252   0.11754  -0.0560   0.0108   1.0000
  15.500   1.1033   0.13134   0.12655  -0.0617   0.0109   1.0000
  15.750   1.0859   0.14162   0.13703  -0.0684   0.0111   1.0000
  16.000   1.0609   0.15568   0.15126  -0.0774   0.0115   1.0000
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