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NREL's S826 Airfoil (s826-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NREL's S826 Airfoil (s826-nr)
Reynolds number: 1,000,000
Max Cl/Cd: 126.69 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s826-nr-1000000-n5.txt
Download as CSV file: xf-s826-nr-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3594   0.04326   0.04108  -0.1254   0.9730   0.0031
 -10.000  -0.3839   0.03675   0.03432  -0.1293   0.9667   0.0031
  -9.750  -0.4009   0.03067   0.02791  -0.1339   0.9607   0.0030
  -9.500  -0.3820   0.02505   0.02182  -0.1434   0.9586   0.0030
  -9.250  -0.3887   0.02327   0.01986  -0.1400   0.9497   0.0030
  -9.000  -0.3649   0.02088   0.01719  -0.1426   0.9473   0.0029
  -8.750  -0.3365   0.01887   0.01494  -0.1451   0.9457   0.0029
  -8.000  -0.2920   0.01562   0.01129  -0.1409   0.9215   0.0029
  -7.750  -0.2614   0.01447   0.01000  -0.1426   0.9146   0.0029
  -7.500  -0.2208   0.01340   0.00879  -0.1462   0.9076   0.0029
  -7.250  -0.1716   0.01240   0.00765  -0.1518   0.8994   0.0030
  -7.000  -0.1253   0.01154   0.00663  -0.1566   0.8828   0.0030
  -6.750  -0.0900   0.01101   0.00590  -0.1588   0.8567   0.0030
  -6.500  -0.0618   0.01064   0.00533  -0.1594   0.8293   0.0031
  -6.000  -0.0088   0.01010   0.00447  -0.1597   0.7832   0.0032
  -5.750   0.0180   0.00984   0.00406  -0.1599   0.7632   0.0033
  -5.500   0.0450   0.00961   0.00369  -0.1601   0.7450   0.0035
  -5.250   0.0726   0.00942   0.00338  -0.1604   0.7286   0.0039
  -5.000   0.1003   0.00926   0.00313  -0.1606   0.7138   0.0047
  -4.750   0.1284   0.00908   0.00290  -0.1610   0.7006   0.0081
  -4.500   0.1567   0.00894   0.00271  -0.1614   0.6885   0.0139
  -4.250   0.1851   0.00883   0.00255  -0.1617   0.6775   0.0186
  -4.000   0.2137   0.00867   0.00239  -0.1622   0.6672   0.0315
  -3.750   0.2425   0.00851   0.00224  -0.1626   0.6572   0.0498
  -3.500   0.2720   0.00827   0.00209  -0.1634   0.6480   0.0907
  -3.250   0.3018   0.00799   0.00192  -0.1642   0.6391   0.1501
  -3.000   0.3354   0.00707   0.00155  -0.1667   0.6302   0.3558
  -2.750   0.3639   0.00706   0.00154  -0.1669   0.6225   0.3847
  -2.500   0.3922   0.00708   0.00154  -0.1671   0.6151   0.3977
  -2.250   0.4205   0.00711   0.00153  -0.1672   0.6088   0.4036
  -2.000   0.4488   0.00715   0.00153  -0.1674   0.6024   0.4111
  -1.500   0.5053   0.00722   0.00155  -0.1677   0.5911   0.4216
  -1.250   0.5335   0.00727   0.00155  -0.1678   0.5854   0.4251
  -1.000   0.5614   0.00734   0.00157  -0.1678   0.5801   0.4286
  -0.750   0.5898   0.00736   0.00159  -0.1680   0.5751   0.4313
  -0.500   0.6179   0.00741   0.00161  -0.1681   0.5702   0.4332
  -0.250   0.6459   0.00747   0.00164  -0.1682   0.5660   0.4352
   0.000   0.6742   0.00750   0.00168  -0.1684   0.5622   0.4375
   0.250   0.7024   0.00754   0.00172  -0.1685   0.5582   0.4398
   0.500   0.7303   0.00761   0.00176  -0.1686   0.5541   0.4420
   0.750   0.7581   0.00768   0.00181  -0.1687   0.5503   0.4438
   1.000   0.7864   0.00771   0.00186  -0.1688   0.5468   0.4460
   1.250   0.8144   0.00776   0.00193  -0.1689   0.5433   0.4484
   1.500   0.8421   0.00783   0.00200  -0.1690   0.5392   0.4511
   1.750   0.8697   0.00790   0.00207  -0.1690   0.5341   0.4539
   2.000   0.8970   0.00798   0.00214  -0.1690   0.5263   0.4564
   2.250   0.9240   0.00808   0.00222  -0.1689   0.5180   0.4585
   2.500   0.9510   0.00818   0.00231  -0.1688   0.5091   0.4611
   2.750   0.9783   0.00827   0.00241  -0.1688   0.5015   0.4638
   3.000   1.0051   0.00837   0.00251  -0.1687   0.4941   0.4667
   3.250   1.0322   0.00846   0.00262  -0.1686   0.4867   0.4699
   3.500   1.0585   0.00860   0.00273  -0.1684   0.4772   0.4727
   3.750   1.0855   0.00869   0.00285  -0.1683   0.4681   0.4756
   4.000   1.1119   0.00881   0.00298  -0.1681   0.4583   0.4787
   4.250   1.1377   0.00898   0.00313  -0.1678   0.4434   0.4818
   4.500   1.1620   0.00924   0.00330  -0.1673   0.4175   0.4849
   4.750   1.1826   0.00979   0.00362  -0.1661   0.3656   0.4877
   5.000   1.2014   0.01051   0.00407  -0.1646   0.3115   0.4904
   5.250   1.2218   0.01108   0.00447  -0.1634   0.2716   0.4937
   5.500   1.2415   0.01168   0.00489  -0.1622   0.2323   0.4973
   5.750   1.2612   0.01225   0.00531  -0.1608   0.1988   0.5009
   6.250   1.3017   0.01321   0.00609  -0.1584   0.1501   0.5078
   6.500   1.3210   0.01371   0.00650  -0.1570   0.1293   0.5114
   6.750   1.3389   0.01419   0.00692  -0.1553   0.1101   0.5151
   7.000   1.3557   0.01467   0.00733  -0.1534   0.0944   0.5183
   7.250   1.3712   0.01524   0.00783  -0.1513   0.0760   0.5219
   7.500   1.3856   0.01587   0.00838  -0.1490   0.0580   0.5258
   7.750   1.3999   0.01650   0.00894  -0.1468   0.0445   0.5298
   8.000   1.4154   0.01708   0.00948  -0.1448   0.0351   0.5336
   8.250   1.4320   0.01759   0.01002  -0.1430   0.0295   0.5378
   8.500   1.4472   0.01818   0.01061  -0.1410   0.0238   0.5426
   8.750   1.4619   0.01881   0.01124  -0.1390   0.0188   0.5476
   9.000   1.4758   0.01948   0.01192  -0.1369   0.0146   0.5526
   9.250   1.4897   0.02017   0.01264  -0.1349   0.0112   0.5584
   9.500   1.5034   0.02088   0.01338  -0.1328   0.0087   0.5638
   9.750   1.5162   0.02166   0.01421  -0.1307   0.0067   0.5694
  10.000   1.5286   0.02248   0.01508  -0.1286   0.0051   0.5755
  10.250   1.5405   0.02334   0.01600  -0.1265   0.0040   0.5815
  10.500   1.5524   0.02424   0.01696  -0.1245   0.0032   0.5886
  10.750   1.5632   0.02523   0.01801  -0.1224   0.0025   0.5955
  11.000   1.5738   0.02625   0.01912  -0.1204   0.0021   0.6036
  11.250   1.5838   0.02738   0.02032  -0.1185   0.0016   0.6122
  11.500   1.5926   0.02862   0.02166  -0.1165   0.0013   0.6224
  11.750   1.6013   0.02992   0.02306  -0.1147   0.0011   0.6336
  12.000   1.6100   0.03129   0.02453  -0.1129   0.0010   0.6457
  12.250   1.6180   0.03276   0.02611  -0.1113   0.0009   0.6591
  12.500   1.6252   0.03436   0.02782  -0.1097   0.0008   0.6739
  12.750   1.6321   0.03606   0.02963  -0.1083   0.0007   0.6913
  13.250   1.6435   0.03991   0.03377  -0.1057   0.0006   0.7419
  13.500   1.6485   0.04203   0.03608  -0.1046   0.0006   0.7848
  13.750   1.6485   0.04397   0.03839  -0.1027   0.0006   1.0000
  14.000   1.6510   0.04650   0.04103  -0.1018   0.0005   1.0000
  14.250   1.6520   0.04929   0.04393  -0.1009   0.0005   1.0000
  14.500   1.6525   0.05223   0.04698  -0.1002   0.0005   1.0000
  14.750   1.6541   0.05512   0.04997  -0.0998   0.0005   1.0000
  15.000   1.6552   0.05815   0.05310  -0.0994   0.0005   1.0000
  15.250   1.6554   0.06137   0.05643  -0.0993   0.0005   1.0000
  15.500   1.6548   0.06479   0.05996  -0.0992   0.0005   1.0000
  15.750   1.6533   0.06842   0.06370  -0.0993   0.0005   1.0000
  16.000   1.6512   0.07224   0.06763  -0.0996   0.0005   1.0000
  16.250   1.6479   0.07634   0.07185  -0.1001   0.0005   1.0000
  16.500   1.6437   0.08064   0.07627  -0.1008   0.0005   1.0000
  16.750   1.6385   0.08523   0.08098  -0.1017   0.0005   1.0000
  17.000   1.6331   0.08996   0.08583  -0.1028   0.0005   1.0000
  17.250   1.6265   0.09498   0.09098  -0.1042   0.0005   1.0000
  17.500   1.6184   0.10036   0.09650  -0.1058   0.0005   1.0000
  17.750   1.6109   0.10574   0.10201  -0.1076   0.0005   1.0000
  18.000   1.6003   0.11181   0.10822  -0.1098   0.0005   1.0000
  18.250   1.5907   0.11783   0.11437  -0.1123   0.0005   1.0000
  18.500   1.5789   0.12438   0.12106  -0.1152   0.0005   1.0000
  18.750   1.5678   0.13095   0.12777  -0.1184   0.0005   1.0000
  19.000   1.5568   0.13760   0.13455  -0.1219   0.0005   1.0000
  19.250   1.5431   0.14501   0.14210  -0.1260   0.0005   1.0000
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