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NREL's S826 Airfoil (s826-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NREL's S826 Airfoil (s826-nr)
Reynolds number: 1,000,000
Max Cl/Cd: 137.7 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s826-nr-1000000.txt
Download as CSV file: xf-s826-nr-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2422   0.03897   0.03715  -0.1086   0.9746   0.0106
  -9.000  -0.2502   0.03262   0.03066  -0.1161   0.9727   0.0106
  -8.750  -0.2655   0.02883   0.02676  -0.1186   0.9657   0.0106
  -8.500  -0.2673   0.02387   0.02161  -0.1271   0.9606   0.0108
  -8.250  -0.2455   0.02030   0.01789  -0.1343   0.9592   0.0110
  -7.250  -0.1958   0.01863   0.01459  -0.1467   0.9470   0.0080
  -7.000  -0.1620   0.01604   0.01178  -0.1486   0.9462   0.0065
  -6.750  -0.1478   0.01436   0.00993  -0.1463   0.9383   0.0061
  -6.500  -0.1153   0.01285   0.00825  -0.1480   0.9354   0.0058
  -6.250  -0.0791   0.01180   0.00711  -0.1504   0.9333   0.0057
  -6.000  -0.0596   0.01108   0.00632  -0.1492   0.9231   0.0057
  -5.750  -0.0210   0.01027   0.00543  -0.1520   0.9192   0.0058
  -5.500   0.0118   0.00965   0.00474  -0.1535   0.9090   0.0060
  -5.250   0.0593   0.00904   0.00404  -0.1581   0.9018   0.0064
  -5.000   0.1065   0.00854   0.00343  -0.1625   0.8893   0.0073
  -4.750   0.1480   0.00798   0.00280  -0.1658   0.8684   0.0219
  -4.500   0.1801   0.00781   0.00253  -0.1669   0.8427   0.0349
  -4.250   0.2086   0.00764   0.00232  -0.1674   0.8177   0.0610
  -4.000   0.2364   0.00743   0.00215  -0.1677   0.7949   0.1075
  -3.500   0.2956   0.00626   0.00160  -0.1701   0.7566   0.3900
  -3.250   0.3224   0.00635   0.00161  -0.1699   0.7393   0.4068
  -3.000   0.3492   0.00646   0.00161  -0.1697   0.7235   0.4157
  -2.750   0.3762   0.00656   0.00164  -0.1696   0.7092   0.4257
  -2.500   0.4034   0.00665   0.00164  -0.1694   0.6965   0.4319
  -2.250   0.4306   0.00673   0.00166  -0.1693   0.6845   0.4364
  -2.000   0.4580   0.00683   0.00168  -0.1693   0.6733   0.4415
  -1.750   0.4857   0.00690   0.00168  -0.1693   0.6633   0.4458
  -1.500   0.5132   0.00697   0.00171  -0.1693   0.6539   0.4495
  -1.250   0.5409   0.00704   0.00173  -0.1693   0.6447   0.4525
  -1.000   0.5686   0.00712   0.00176  -0.1693   0.6365   0.4560
  -0.750   0.5962   0.00721   0.00178  -0.1693   0.6285   0.4581
  -0.500   0.6242   0.00724   0.00179  -0.1694   0.6217   0.4604
  -0.250   0.6520   0.00728   0.00182  -0.1695   0.6149   0.4627
   0.000   0.6798   0.00735   0.00186  -0.1695   0.6091   0.4649
   0.250   0.7079   0.00740   0.00190  -0.1696   0.6032   0.4672
   0.500   0.7355   0.00749   0.00195  -0.1697   0.5976   0.4697
   0.750   0.7636   0.00755   0.00200  -0.1698   0.5926   0.4720
   1.000   0.7916   0.00761   0.00205  -0.1699   0.5877   0.4742
   1.250   0.8192   0.00767   0.00212  -0.1699   0.5831   0.4770
   1.500   0.8472   0.00773   0.00219  -0.1700   0.5784   0.4797
   1.750   0.8749   0.00779   0.00226  -0.1701   0.5724   0.4826
   2.000   0.9017   0.00791   0.00234  -0.1700   0.5656   0.4854
   2.250   0.9294   0.00796   0.00241  -0.1700   0.5588   0.4880
   2.750   0.9839   0.00809   0.00257  -0.1699   0.5455   0.4942
   3.000   1.0110   0.00818   0.00267  -0.1698   0.5396   0.4973
   3.250   1.0381   0.00827   0.00277  -0.1698   0.5338   0.5006
   3.500   1.0652   0.00836   0.00286  -0.1697   0.5271   0.5036
   3.750   1.0918   0.00846   0.00299  -0.1696   0.5211   0.5075
   4.000   1.1193   0.00851   0.00310  -0.1696   0.5152   0.5112
   4.250   1.1455   0.00863   0.00323  -0.1693   0.5081   0.5148
   4.500   1.1723   0.00872   0.00334  -0.1692   0.5005   0.5182
   4.750   1.1981   0.00885   0.00349  -0.1689   0.4913   0.5222
   5.000   1.2245   0.00894   0.00363  -0.1687   0.4809   0.5262
   5.250   1.2503   0.00908   0.00378  -0.1684   0.4694   0.5303
   5.500   1.2750   0.00926   0.00394  -0.1679   0.4523   0.5342
   5.750   1.2983   0.00953   0.00415  -0.1671   0.4235   0.5389
   6.000   1.3171   0.01013   0.00451  -0.1656   0.3703   0.5434
   6.250   1.3327   0.01100   0.00506  -0.1636   0.3100   0.5476
   6.500   1.3482   0.01185   0.00565  -0.1616   0.2552   0.5519
   6.750   1.3643   0.01261   0.00620  -0.1596   0.2111   0.5566
   7.000   1.3792   0.01337   0.00675  -0.1575   0.1728   0.5614
   7.250   1.3918   0.01410   0.00731  -0.1549   0.1369   0.5660
   7.500   1.4046   0.01481   0.00788  -0.1523   0.1086   0.5712
   7.750   1.4188   0.01546   0.00843  -0.1500   0.0883   0.5768
   8.000   1.4336   0.01606   0.00899  -0.1479   0.0727   0.5826
   8.250   1.4489   0.01665   0.00955  -0.1458   0.0609   0.5891
   8.500   1.4635   0.01726   0.01013  -0.1437   0.0505   0.5958
   8.750   1.4779   0.01789   0.01076  -0.1416   0.0420   0.6036
   9.000   1.4917   0.01857   0.01143  -0.1395   0.0346   0.6118
   9.250   1.5064   0.01919   0.01208  -0.1375   0.0295   0.6213
   9.500   1.5199   0.01990   0.01283  -0.1354   0.0244   0.6313
   9.750   1.5319   0.02071   0.01365  -0.1331   0.0194   0.6423
  10.000   1.5433   0.02157   0.01454  -0.1308   0.0151   0.6548
  10.250   1.5536   0.02251   0.01553  -0.1285   0.0112   0.6692
  10.500   1.5630   0.02357   0.01664  -0.1261   0.0079   0.6859
  10.750   1.5706   0.02478   0.01793  -0.1235   0.0052   0.7060
  11.000   1.5757   0.02622   0.01948  -0.1208   0.0034   0.7304
  11.250   1.5819   0.02761   0.02103  -0.1183   0.0026   0.7655
  11.500   1.5855   0.02925   0.02292  -0.1158   0.0022   0.8291
  11.750   1.5889   0.03033   0.02428  -0.1129   0.0020   1.0000
  12.000   1.5955   0.03193   0.02597  -0.1110   0.0019   1.0000
  12.250   1.6012   0.03366   0.02779  -0.1092   0.0018   1.0000
  12.500   1.6063   0.03553   0.02974  -0.1075   0.0017   1.0000
  12.750   1.6109   0.03753   0.03183  -0.1060   0.0017   1.0000
  13.000   1.6145   0.03970   0.03409  -0.1046   0.0016   1.0000
  13.250   1.6173   0.04203   0.03652  -0.1033   0.0015   1.0000
  13.500   1.6194   0.04455   0.03914  -0.1022   0.0015   1.0000
  13.750   1.6204   0.04730   0.04199  -0.1012   0.0015   1.0000
  14.000   1.6203   0.05025   0.04505  -0.1004   0.0014   1.0000
  14.250   1.6189   0.05348   0.04840  -0.0998   0.0014   1.0000
  14.500   1.6166   0.05694   0.05197  -0.0993   0.0014   1.0000
  14.750   1.6129   0.06070   0.05586  -0.0991   0.0014   1.0000
  15.000   1.6095   0.06452   0.05979  -0.0990   0.0014   1.0000
  15.250   1.6033   0.06887   0.06428  -0.0992   0.0013   1.0000
  15.500   1.5972   0.07335   0.06889  -0.0997   0.0013   1.0000
  15.750   1.5902   0.07810   0.07377  -0.1003   0.0013   1.0000
  16.000   1.5826   0.08306   0.07886  -0.1012   0.0013   1.0000
  16.250   1.5737   0.08839   0.08433  -0.1024   0.0013   1.0000
  16.500   1.5653   0.09379   0.08986  -0.1038   0.0013   1.0000
  16.750   1.5548   0.09964   0.09586  -0.1056   0.0013   1.0000
  17.000   1.5465   0.10526   0.10160  -0.1074   0.0013   1.0000
  17.250   1.5377   0.11109   0.10757  -0.1096   0.0013   1.0000
  17.500   1.5262   0.11757   0.11419  -0.1122   0.0013   1.0000
  17.750   1.5168   0.12376   0.12050  -0.1150   0.0013   1.0000
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