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NREL's S826 Airfoil (s826-nr) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NREL's S826 Airfoil (s826-nr)
Reynolds number: 500,000
Max Cl/Cd: 113.97 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s826-nr-500000.txt
Download as CSV file: xf-s826-nr-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S826 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3176   0.08270   0.08057  -0.0679   0.9870   0.0180
  -8.750  -0.3161   0.07273   0.07056  -0.0792   0.9845   0.0182
  -8.500  -0.3252   0.06502   0.06276  -0.0878   0.9776   0.0183
  -8.250  -0.3274   0.05806   0.05561  -0.0994   0.9719   0.0185
  -8.000  -0.3218   0.05208   0.04936  -0.1099   0.9613   0.0187
  -7.750  -0.2984   0.04653   0.04338  -0.1202   0.9583   0.0188
  -7.500  -0.2989   0.03956   0.03629  -0.1225   0.9491   0.0196
  -7.250  -0.2695   0.03649   0.03310  -0.1268   0.9469   0.0202
  -7.000  -0.2360   0.03348   0.02989  -0.1314   0.9455   0.0211
  -6.750  -0.2182   0.03109   0.02731  -0.1314   0.9368   0.0222
  -6.500  -0.1823   0.02080   0.01570  -0.1337   0.9347   0.0105
  -6.250  -0.1474   0.01867   0.01344  -0.1357   0.9331   0.0101
  -6.000  -0.1243   0.01705   0.01168  -0.1351   0.9259   0.0099
  -5.750  -0.0910   0.01562   0.01014  -0.1365   0.9223   0.0099
  -5.500  -0.0539   0.01439   0.00883  -0.1389   0.9200   0.0100
  -5.250  -0.0266   0.01350   0.00785  -0.1392   0.9116   0.0104
  -5.000   0.0125   0.01218   0.00648  -0.1425   0.9075   0.0116
  -4.750   0.0480   0.01133   0.00556  -0.1446   0.9001   0.0151
  -4.500   0.0899   0.01043   0.00465  -0.1480   0.8944   0.0311
  -4.250   0.1329   0.00970   0.00403  -0.1517   0.8872   0.0664
  -4.000   0.1896   0.00778   0.00306  -0.1601   0.8808   0.3702
  -3.750   0.2353   0.00769   0.00290  -0.1638   0.8687   0.4129
  -3.500   0.2769   0.00771   0.00277  -0.1666   0.8523   0.4302
  -3.250   0.3125   0.00787   0.00276  -0.1681   0.8324   0.4443
  -3.000   0.3426   0.00804   0.00282  -0.1684   0.8112   0.4536
  -2.750   0.3716   0.00820   0.00278  -0.1686   0.7917   0.4594
  -2.500   0.3988   0.00834   0.00284  -0.1684   0.7736   0.4647
  -2.250   0.4259   0.00852   0.00288  -0.1681   0.7566   0.4705
  -2.000   0.4530   0.00864   0.00286  -0.1680   0.7412   0.4748
  -1.750   0.4798   0.00873   0.00289  -0.1678   0.7274   0.4783
  -1.500   0.5068   0.00886   0.00292  -0.1676   0.7151   0.4819
  -1.250   0.5342   0.00893   0.00291  -0.1676   0.7035   0.4846
  -1.000   0.5618   0.00900   0.00289  -0.1676   0.6932   0.4868
  -0.750   0.5895   0.00909   0.00287  -0.1677   0.6840   0.4889
  -0.500   0.6170   0.00911   0.00287  -0.1677   0.6748   0.4910
  -0.250   0.6445   0.00917   0.00290  -0.1677   0.6667   0.4931
   0.000   0.6721   0.00925   0.00295  -0.1677   0.6590   0.4957
   0.250   0.7000   0.00934   0.00300  -0.1678   0.6522   0.4985
   0.500   0.7279   0.00942   0.00304  -0.1679   0.6456   0.5012
   0.750   0.7562   0.00954   0.00309  -0.1681   0.6399   0.5036
   1.000   0.7839   0.00955   0.00314  -0.1682   0.6338   0.5062
   1.250   0.8117   0.00964   0.00323  -0.1683   0.6283   0.5088
   1.500   0.8399   0.00974   0.00333  -0.1684   0.6234   0.5119
   1.750   0.8678   0.00981   0.00342  -0.1685   0.6184   0.5152
   2.000   0.8959   0.00994   0.00351  -0.1687   0.6135   0.5182
   2.250   0.9236   0.01000   0.00362  -0.1688   0.6081   0.5211
   2.500   0.9506   0.01006   0.00372  -0.1687   0.6018   0.5241
   2.750   0.9780   0.01020   0.00384  -0.1687   0.5954   0.5275
   3.000   1.0041   0.01025   0.00394  -0.1684   0.5878   0.5314
   3.250   1.0310   0.01038   0.00405  -0.1683   0.5806   0.5351
   3.500   1.0571   0.01041   0.00417  -0.1680   0.5735   0.5385
   3.750   1.0838   0.01055   0.00431  -0.1679   0.5671   0.5423
   4.000   1.1099   0.01062   0.00445  -0.1676   0.5600   0.5465
   4.250   1.1361   0.01073   0.00457  -0.1673   0.5530   0.5504
   4.500   1.1622   0.01080   0.00474  -0.1671   0.5463   0.5543
   4.750   1.1878   0.01092   0.00490  -0.1667   0.5386   0.5589
   5.250   1.2379   0.01116   0.00524  -0.1657   0.5212   0.5685
   5.500   1.2623   0.01124   0.00542  -0.1651   0.5105   0.5736
   6.000   1.3099   0.01151   0.00581  -0.1636   0.4857   0.5837
   6.250   1.3323   0.01169   0.00602  -0.1626   0.4679   0.5894
   6.500   1.3530   0.01193   0.00625  -0.1613   0.4431   0.5951
   6.750   1.3695   0.01237   0.00658  -0.1592   0.3991   0.6006
   7.000   1.3771   0.01337   0.00721  -0.1557   0.3317   0.6065
   7.250   1.3843   0.01442   0.00797  -0.1522   0.2739   0.6122
   7.500   1.3934   0.01541   0.00873  -0.1491   0.2269   0.6189
   7.750   1.4033   0.01635   0.00950  -0.1461   0.1885   0.6260
   8.000   1.4134   0.01727   0.01028  -0.1433   0.1553   0.6338
   8.250   1.4234   0.01819   0.01110  -0.1405   0.1276   0.6419
   8.500   1.4335   0.01911   0.01193  -0.1378   0.1051   0.6512
   8.750   1.4449   0.01996   0.01275  -0.1354   0.0883   0.6611
   9.000   1.4561   0.02082   0.01362  -0.1330   0.0746   0.6726
   9.250   1.4667   0.02174   0.01454  -0.1305   0.0625   0.6858
   9.500   1.4766   0.02271   0.01553  -0.1281   0.0522   0.7015
   9.750   1.4858   0.02375   0.01660  -0.1257   0.0430   0.7211
  10.000   1.4950   0.02481   0.01773  -0.1233   0.0354   0.7472
  10.250   1.5047   0.02584   0.01889  -0.1211   0.0291   0.7870
  10.500   1.5061   0.02664   0.01998  -0.1173   0.0245   1.0000
  10.750   1.5122   0.02814   0.02146  -0.1150   0.0194   1.0000
  11.000   1.5174   0.02976   0.02309  -0.1128   0.0151   1.0000
  11.250   1.5219   0.03150   0.02487  -0.1106   0.0118   1.0000
  11.500   1.5249   0.03348   0.02692  -0.1085   0.0094   1.0000
  11.750   1.5244   0.03589   0.02940  -0.1063   0.0075   1.0000
  12.000   1.5281   0.03801   0.03161  -0.1047   0.0062   1.0000
  12.250   1.5228   0.04114   0.03486  -0.1027   0.0054   1.0000
  12.500   1.5260   0.04352   0.03736  -0.1015   0.0049   1.0000
  12.750   1.5275   0.04618   0.04013  -0.1004   0.0045   1.0000
  13.000   1.5283   0.04901   0.04307  -0.0995   0.0042   1.0000
  13.250   1.5274   0.05214   0.04631  -0.0987   0.0040   1.0000
  13.500   1.5224   0.05588   0.05017  -0.0981   0.0038   1.0000
  13.750   1.5124   0.06044   0.05488  -0.0977   0.0037   1.0000
  14.000   1.5058   0.06468   0.05925  -0.0975   0.0036   1.0000
  14.250   1.5042   0.06837   0.06307  -0.0975   0.0035   1.0000
  14.500   1.5017   0.07230   0.06713  -0.0976   0.0035   1.0000
  14.750   1.4984   0.07642   0.07140  -0.0980   0.0034   1.0000
  15.000   1.4947   0.08070   0.07581  -0.0985   0.0034   1.0000
  15.250   1.4902   0.08521   0.08046  -0.0992   0.0033   1.0000
  15.500   1.4855   0.08985   0.08525  -0.1001   0.0033   1.0000
  15.750   1.4805   0.09464   0.09018  -0.1011   0.0032   1.0000
  16.000   1.4749   0.09960   0.09531  -0.1024   0.0032   1.0000
  16.250   1.4688   0.10477   0.10064  -0.1039   0.0032   1.0000
  16.500   1.4624   0.11007   0.10609  -0.1056   0.0032   1.0000
  16.750   1.4553   0.11562   0.11180  -0.1077   0.0031   1.0000
  17.000   1.4480   0.12129   0.11764  -0.1100   0.0032   1.0000
  17.250   1.4400   0.12723   0.12374  -0.1127   0.0032   1.0000
  17.500   1.4310   0.13353   0.13022  -0.1157   0.0032   1.0000
  17.750   1.4225   0.13987   0.13673  -0.1191   0.0032   1.0000
  18.000   1.4124   0.14675   0.14378  -0.1230   0.0032   1.0000
  18.250   1.4025   0.15371   0.15090  -0.1272   0.0032   1.0000
  18.500   1.3913   0.16121   0.15858  -0.1320   0.0032   1.0000
  18.750   1.3805   0.16885   0.16638  -0.1371   0.0032   1.0000
  19.000   1.3701   0.17661   0.17429  -0.1424   0.0033   1.0000
  19.250   1.3582   0.18507   0.18290  -0.1483   0.0033   1.0000
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