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NREL's S831 Airfoil (s831-nr) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NREL's S831 Airfoil (s831-nr)
Reynolds number: 500,000
Max Cl/Cd: 112.58 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s831-nr-500000-n5.txt
Download as CSV file: xf-s831-nr-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S831 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250   0.0934   0.08653   0.08275  -0.1706   0.7790   0.0113
 -11.000   0.0953   0.08297   0.07919  -0.1721   0.7759   0.0113
 -10.750   0.0974   0.07952   0.07575  -0.1735   0.7723   0.0113
 -10.500   0.0985   0.07596   0.07219  -0.1750   0.7689   0.0113
 -10.250   0.0986   0.07216   0.06839  -0.1768   0.7656   0.0113
 -10.000   0.0973   0.06792   0.06414  -0.1793   0.7626   0.0113
  -9.750   0.0910   0.06311   0.05934  -0.1823   0.7595   0.0113
  -9.500   0.0825   0.05920   0.05539  -0.1842   0.7561   0.0113
  -8.500   0.0449   0.03135   0.02749  -0.1734   0.7381   0.0080
  -8.000   0.0061   0.04221   0.03793  -0.1766   0.7378   0.0079
  -7.750   0.0063   0.04005   0.03562  -0.1749   0.7353   0.0076
  -7.250   0.0039   0.03099   0.02599  -0.1689   0.7304   0.0057
  -7.000   0.0128   0.02856   0.02333  -0.1672   0.7281   0.0056
  -6.750   0.0244   0.02579   0.02028  -0.1655   0.7260   0.0055
  -6.500   0.0381   0.02248   0.01662  -0.1637   0.7240   0.0053
  -6.250   0.0559   0.01956   0.01328  -0.1622   0.7223   0.0051
  -6.000   0.0774   0.01761   0.01100  -0.1613   0.7207   0.0051
  -5.750   0.0996   0.01637   0.00956  -0.1605   0.7190   0.0051
  -5.500   0.1217   0.01551   0.00857  -0.1598   0.7173   0.0051
  -5.250   0.1434   0.01478   0.00773  -0.1590   0.7154   0.0051
  -5.000   0.1652   0.01418   0.00704  -0.1583   0.7135   0.0052
  -4.750   0.1875   0.01367   0.00646  -0.1578   0.7116   0.0053
  -4.500   0.2107   0.01324   0.00596  -0.1575   0.7097   0.0054
  -4.250   0.2349   0.01286   0.00550  -0.1574   0.7081   0.0056
  -4.000   0.2603   0.01255   0.00511  -0.1575   0.7067   0.0058
  -3.750   0.2856   0.01220   0.00472  -0.1576   0.7052   0.0066
  -3.500   0.3111   0.01196   0.00445  -0.1577   0.7037   0.0075
  -3.250   0.3371   0.01170   0.00418  -0.1578   0.7022   0.0113
  -3.000   0.3635   0.01150   0.00401  -0.1581   0.7006   0.0189
  -2.750   0.3902   0.01134   0.00390  -0.1585   0.6991   0.0307
  -2.500   0.4173   0.01120   0.00380  -0.1589   0.6976   0.0459
  -2.250   0.4447   0.01104   0.00365  -0.1594   0.6962   0.0622
  -2.000   0.4730   0.00916   0.00316  -0.1623   0.6948   0.5295
  -1.750   0.5016   0.00911   0.00325  -0.1628   0.6934   0.6047
  -1.500   0.5305   0.00919   0.00330  -0.1634   0.6921   0.6273
  -1.250   0.5585   0.00926   0.00335  -0.1638   0.6908   0.6390
  -1.000   0.5860   0.00934   0.00339  -0.1641   0.6894   0.6496
  -0.750   0.6130   0.00942   0.00348  -0.1642   0.6881   0.6584
  -0.500   0.6407   0.00950   0.00351  -0.1646   0.6867   0.6648
  -0.250   0.6680   0.00955   0.00356  -0.1649   0.6853   0.6679
   0.000   0.6956   0.00959   0.00359  -0.1652   0.6840   0.6697
   0.250   0.7234   0.00965   0.00362  -0.1657   0.6828   0.6718
   0.500   0.7513   0.00970   0.00365  -0.1661   0.6815   0.6740
   0.750   0.7795   0.00976   0.00368  -0.1666   0.6803   0.6761
   1.000   0.8082   0.00983   0.00372  -0.1673   0.6791   0.6781
   1.250   0.8373   0.00990   0.00376  -0.1680   0.6779   0.6800
   1.500   0.8653   0.00997   0.00384  -0.1685   0.6767   0.6817
   1.750   0.8911   0.01004   0.00395  -0.1686   0.6755   0.6835
   2.000   0.9172   0.01012   0.00406  -0.1687   0.6742   0.6855
   2.250   0.9435   0.01020   0.00417  -0.1688   0.6729   0.6877
   2.500   0.9699   0.01028   0.00429  -0.1690   0.6716   0.6902
   2.750   0.9965   0.01037   0.00440  -0.1693   0.6703   0.6927
   3.250   1.0495   0.01054   0.00462  -0.1697   0.6676   0.6969
   3.500   1.0763   0.01062   0.00476  -0.1700   0.6663   0.6989
   3.750   1.1038   0.01072   0.00489  -0.1704   0.6653   0.7011
   4.000   1.1322   0.01082   0.00502  -0.1711   0.6642   0.7034
   4.250   1.1615   0.01094   0.00517  -0.1719   0.6632   0.7059
   4.500   1.1868   0.01106   0.00535  -0.1719   0.6620   0.7085
   4.750   1.2089   0.01119   0.00556  -0.1713   0.6604   0.7111
   5.000   1.2318   0.01131   0.00578  -0.1708   0.6589   0.7134
   5.250   1.2552   0.01144   0.00600  -0.1704   0.6574   0.7159
   5.500   1.2783   0.01157   0.00620  -0.1699   0.6558   0.7185
   5.750   1.2982   0.01161   0.00629  -0.1687   0.6524   0.7213
   6.000   1.3078   0.01162   0.00634  -0.1653   0.6452   0.7243
   6.250   1.3138   0.01167   0.00637  -0.1611   0.6345   0.7271
   6.500   1.3139   0.01192   0.00671  -0.1559   0.6229   0.7300
   6.750   1.3233   0.01219   0.00704  -0.1528   0.6133   0.7333
   7.000   1.3381   0.01244   0.00731  -0.1508   0.6060   0.7366
   7.250   1.3505   0.01279   0.00775  -0.1484   0.5978   0.7400
   7.500   1.3623   0.01316   0.00818  -0.1460   0.5883   0.7429
   7.750   1.3709   0.01365   0.00871  -0.1430   0.5749   0.7458
   8.000   1.3746   0.01434   0.00940  -0.1393   0.5545   0.7492
   8.250   1.3625   0.01569   0.01060  -0.1330   0.5173   0.7531
   8.500   1.3471   0.01747   0.01222  -0.1267   0.4812   0.7569
   8.750   1.3194   0.02012   0.01465  -0.1190   0.4367   0.7605
   9.000   1.3006   0.02267   0.01704  -0.1132   0.3992   0.7642
   9.250   1.2822   0.02544   0.01962  -0.1078   0.3598   0.7680
   9.500   1.2696   0.02805   0.02207  -0.1035   0.3227   0.7715
   9.750   1.2592   0.03062   0.02449  -0.0997   0.2862   0.7747
  10.000   1.2509   0.03317   0.02686  -0.0964   0.2475   0.7781
  10.250   1.2491   0.03532   0.02888  -0.0938   0.2169   0.7819
  10.500   1.2486   0.03746   0.03088  -0.0916   0.1871   0.7858
  11.000   1.2530   0.04143   0.03463  -0.0878   0.1334   0.7935
  11.250   1.2583   0.04323   0.03635  -0.0864   0.1122   0.7977
  11.750   1.2726   0.04663   0.03967  -0.0839   0.0808   0.8058
  12.000   1.2815   0.04822   0.04126  -0.0830   0.0700   0.8103
  12.250   1.2905   0.04983   0.04286  -0.0820   0.0598   0.8152
  12.500   1.2998   0.05141   0.04445  -0.0811   0.0506   0.8202
  12.750   1.3082   0.05310   0.04615  -0.0802   0.0421   0.8258
  13.250   1.3235   0.05669   0.04973  -0.0784   0.0255   0.8376
  13.500   1.3311   0.05854   0.05160  -0.0776   0.0198   0.8442
  13.750   1.3381   0.06045   0.05353  -0.0768   0.0145   0.8513
  14.000   1.3462   0.06226   0.05539  -0.0761   0.0113   0.8598
  14.250   1.3549   0.06399   0.05722  -0.0754   0.0096   0.8713
  14.500   1.3624   0.06586   0.05918  -0.0746   0.0078   0.8879
  14.750   1.3678   0.06755   0.06101  -0.0736   0.0061   0.9819
  15.000   1.3761   0.06949   0.06301  -0.0731   0.0053   1.0000
  15.250   1.3832   0.07165   0.06523  -0.0727   0.0043   1.0000
  15.500   1.3912   0.07371   0.06739  -0.0724   0.0036   1.0000
  15.750   1.3974   0.07600   0.06975  -0.0721   0.0029   1.0000
  16.000   1.4032   0.07837   0.07219  -0.0718   0.0025   1.0000
  16.250   1.4091   0.08076   0.07467  -0.0716   0.0021   1.0000
  16.500   1.4138   0.08331   0.07731  -0.0714   0.0018   1.0000
  16.750   1.4166   0.08613   0.08022  -0.0711   0.0015   1.0000
  17.000   1.4207   0.08884   0.08304  -0.0711   0.0014   1.0000
  17.250   1.4244   0.09159   0.08591  -0.0711   0.0013   1.0000
  17.500   1.4269   0.09458   0.08900  -0.0712   0.0012   1.0000
  17.750   1.4291   0.09763   0.09217  -0.0714   0.0011   1.0000
  18.000   1.4303   0.10085   0.09553  -0.0717   0.0010   1.0000
  18.250   1.4309   0.10421   0.09901  -0.0721   0.0010   1.0000
  18.500   1.4307   0.10770   0.10262  -0.0726   0.0009   1.0000
  18.750   1.4302   0.11125   0.10629  -0.0733   0.0009   1.0000
  19.000   1.4274   0.11521   0.11037  -0.0741   0.0009   1.0000
  19.250   1.4253   0.11911   0.11440  -0.0751   0.0009   1.0000
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