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NREL's S826 Airfoil (s826-nr) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NREL's S826 Airfoil (s826-nr)
Reynolds number: 200,000
Max Cl/Cd: 82.99 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s826-nr-200000.txt
Download as CSV file: xf-s826-nr-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3583   0.11465   0.11128  -0.0402   1.0000   0.0395
  -9.750  -0.3654   0.11094   0.10764  -0.0416   1.0000   0.0408
  -9.500  -0.3768   0.10703   0.10380  -0.0439   1.0000   0.0416
  -8.000  -0.4143   0.08187   0.07893  -0.0530   0.9943   0.0442
  -7.750  -0.3999   0.07791   0.07496  -0.0571   0.9886   0.0456
  -7.500  -0.3229   0.05264   0.04949  -0.0878   0.9587   0.0527
  -7.250  -0.3209   0.04837   0.04463  -0.0989   0.9462   0.0536
  -7.000  -0.3635   0.05786   0.05386  -0.0990   0.9551   0.0533
  -6.750  -0.3458   0.05003   0.04586  -0.1048   0.9486   0.0553
  -6.500  -0.3140   0.04600   0.04184  -0.1088   0.9459   0.0579
  -6.250  -0.2438   0.02698   0.02258  -0.1139   0.9226   0.0693
  -6.000  -0.2095   0.02327   0.01876  -0.1177   0.9200   0.0739
  -5.750  -0.1965   0.02832   0.02202  -0.1199   0.9329   0.0241
  -5.500  -0.1671   0.02565   0.01909  -0.1207   0.9256   0.0233
  -5.250  -0.1295   0.02341   0.01661  -0.1224   0.9220   0.0234
  -5.000  -0.0891   0.02174   0.01475  -0.1245   0.9196   0.0245
  -4.750  -0.0600   0.02016   0.01323  -0.1252   0.9111   0.0283
  -4.500  -0.0172   0.01870   0.01179  -0.1287   0.9078   0.0366
  -4.250   0.0314   0.01713   0.01022  -0.1336   0.9057   0.0560
  -4.000   0.0727   0.01560   0.00882  -0.1377   0.8976   0.1040
  -3.750   0.1246   0.01428   0.00850  -0.1440   0.8948   0.4468
  -3.500   0.1604   0.01464   0.00878  -0.1446   0.8892   0.4745
  -3.250   0.1916   0.01503   0.00920  -0.1441   0.8814   0.4922
  -3.000   0.2339   0.01508   0.00917  -0.1462   0.8778   0.5055
  -2.750   0.2662   0.01518   0.00927  -0.1464   0.8674   0.5139
  -2.500   0.3085   0.01513   0.00914  -0.1487   0.8607   0.5232
  -2.250   0.3485   0.01503   0.00894  -0.1509   0.8511   0.5305
  -2.000   0.3891   0.01472   0.00847  -0.1537   0.8400   0.5353
  -1.750   0.4284   0.01446   0.00808  -0.1561   0.8288   0.5372
  -1.500   0.4660   0.01429   0.00778  -0.1581   0.8174   0.5396
  -1.250   0.5008   0.01418   0.00752  -0.1597   0.8052   0.5425
  -1.000   0.5328   0.01409   0.00728  -0.1608   0.7923   0.5457
  -0.750   0.5650   0.01401   0.00703  -0.1621   0.7804   0.5489
  -0.500   0.5947   0.01399   0.00694  -0.1626   0.7699   0.5509
  -0.250   0.6253   0.01402   0.00688  -0.1632   0.7608   0.5534
   0.000   0.6527   0.01407   0.00691  -0.1633   0.7507   0.5564
   0.250   0.6829   0.01413   0.00687  -0.1640   0.7424   0.5600
   0.500   0.7129   0.01416   0.00680  -0.1648   0.7338   0.5637
   0.750   0.7410   0.01422   0.00685  -0.1650   0.7263   0.5661
   1.000   0.7691   0.01430   0.00693  -0.1652   0.7192   0.5689
   1.250   0.7980   0.01442   0.00704  -0.1656   0.7129   0.5725
   1.500   0.8264   0.01452   0.00712  -0.1659   0.7058   0.5768
   1.750   0.8571   0.01463   0.00717  -0.1667   0.7006   0.5803
   2.000   0.8827   0.01474   0.00738  -0.1665   0.6941   0.5833
   2.250   0.9116   0.01487   0.00754  -0.1668   0.6886   0.5870
   2.500   0.9404   0.01503   0.00770  -0.1673   0.6832   0.5915
   2.750   0.9672   0.01515   0.00788  -0.1673   0.6767   0.5956
   3.000   0.9966   0.01530   0.00805  -0.1677   0.6714   0.5996
   3.250   1.0219   0.01545   0.00831  -0.1674   0.6646   0.6042
   3.500   1.0510   0.01557   0.00841  -0.1678   0.6581   0.6091
   3.750   1.0759   0.01569   0.00864  -0.1672   0.6502   0.6129
   4.000   1.1039   0.01577   0.00874  -0.1672   0.6421   0.6179
   4.250   1.1286   0.01589   0.00894  -0.1667   0.6330   0.6238
   4.500   1.1561   0.01597   0.00907  -0.1666   0.6252   0.6287
   4.750   1.1800   0.01607   0.00930  -0.1658   0.6160   0.6347
   5.000   1.2058   0.01617   0.00946  -0.1655   0.6072   0.6404
   5.250   1.2312   0.01624   0.00962  -0.1649   0.5980   0.6461
   5.750   1.2793   0.01641   0.01002  -0.1634   0.5781   0.6590
   6.000   1.3038   0.01648   0.01014  -0.1627   0.5667   0.6671
   6.250   1.3244   0.01652   0.01035  -0.1612   0.5537   0.6740
   6.500   1.3456   0.01660   0.01054  -0.1598   0.5397   0.6830
   6.750   1.3652   0.01665   0.01074  -0.1581   0.5241   0.6907
   7.000   1.3843   0.01675   0.01093  -0.1563   0.5062   0.7000
   7.250   1.4001   0.01687   0.01119  -0.1539   0.4831   0.7097
   7.500   1.4138   0.01705   0.01147  -0.1511   0.4533   0.7197
   7.750   1.4222   0.01744   0.01179  -0.1474   0.4051   0.7312
   8.000   1.4191   0.01836   0.01238  -0.1418   0.3431   0.7436
   8.250   1.4136   0.01971   0.01345  -0.1363   0.2875   0.7575
   8.500   1.4102   0.02115   0.01467  -0.1313   0.2392   0.7736
   8.750   1.4075   0.02263   0.01598  -0.1268   0.2005   0.7943
   9.000   1.4062   0.02402   0.01731  -0.1225   0.1692   0.8261
   9.250   1.3994   0.02502   0.01839  -0.1172   0.1481   1.0000
   9.500   1.4024   0.02677   0.02000  -0.1144   0.1259   1.0000
   9.750   1.4047   0.02858   0.02171  -0.1117   0.1082   1.0000
  10.000   1.4069   0.03045   0.02352  -0.1091   0.0940   1.0000
  10.250   1.4098   0.03236   0.02540  -0.1068   0.0819   1.0000
  10.500   1.4128   0.03435   0.02741  -0.1047   0.0714   1.0000
  10.750   1.4137   0.03661   0.02968  -0.1026   0.0628   1.0000
  11.000   1.4128   0.03912   0.03217  -0.1007   0.0551   1.0000
  11.250   1.4174   0.04128   0.03443  -0.0992   0.0475   1.0000
  11.500   1.4148   0.04424   0.03742  -0.0975   0.0415   1.0000
  11.750   1.4151   0.04699   0.04019  -0.0963   0.0356   1.0000
  12.000   1.4154   0.04992   0.04324  -0.0950   0.0306   1.0000
  12.250   1.4131   0.05318   0.04649  -0.0941   0.0270   1.0000
  12.500   1.4152   0.05609   0.04955  -0.0932   0.0235   1.0000
  12.750   1.4162   0.05911   0.05261  -0.0927   0.0209   1.0000
  13.000   1.4144   0.06270   0.05628  -0.0918   0.0189   1.0000
  13.250   1.4175   0.06568   0.05942  -0.0914   0.0170   1.0000
  13.500   1.4181   0.06895   0.06275  -0.0914   0.0155   1.0000
  13.750   1.4174   0.07261   0.06652  -0.0910   0.0141   1.0000
  14.000   1.4194   0.07593   0.07003  -0.0909   0.0130   1.0000
  14.250   1.4207   0.07943   0.07368  -0.0909   0.0122   1.0000
  14.500   1.4212   0.08304   0.07740  -0.0910   0.0116   1.0000
  14.750   1.4216   0.08676   0.08119  -0.0911   0.0111   1.0000
  15.000   1.4224   0.09084   0.08542  -0.0906   0.0108   1.0000
  15.250   1.4171   0.09563   0.09050  -0.0915   0.0105   1.0000
  15.500   1.4108   0.10071   0.09585  -0.0927   0.0104   1.0000
  15.750   1.4030   0.10612   0.10152  -0.0943   0.0103   1.0000
  16.000   1.3929   0.11204   0.10771  -0.0964   0.0102   1.0000
  16.250   1.3808   0.11848   0.11441  -0.0991   0.0101   1.0000
  16.500   1.3685   0.12515   0.12132  -0.1023   0.0101   1.0000
  16.750   1.3543   0.13245   0.12887  -0.1063   0.0101   1.0000
  17.000   1.3409   0.13982   0.13645  -0.1106   0.0102   1.0000
  17.250   1.3266   0.14774   0.14457  -0.1156   0.0103   1.0000
  17.500   1.3105   0.15658   0.15363  -0.1216   0.0103   1.0000
  17.750   1.2969   0.16517   0.16238  -0.1276   0.0105   1.0000
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