Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NREL's S831 Airfoil (s831-nr) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NREL's S831 Airfoil (s831-nr)
Reynolds number: 500,000
Max Cl/Cd: 113.91 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s831-nr-500000.txt
Download as CSV file: xf-s831-nr-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750   0.1271   0.09697   0.09374  -0.1548   0.8260   0.0148
 -12.500   0.1268   0.09350   0.09024  -0.1569   0.8230   0.0150
 -12.250   0.1277   0.09001   0.08673  -0.1587   0.8200   0.0151
 -12.000   0.1299   0.08660   0.08333  -0.1601   0.8167   0.0152
 -11.750   0.1324   0.08314   0.07986  -0.1615   0.8135   0.0152
 -11.500   0.1348   0.07958   0.07628  -0.1629   0.8106   0.0152
 -11.250   0.1368   0.07570   0.07236  -0.1632   0.8079   0.0155
 -11.000   0.1428   0.07294   0.06960  -0.1636   0.8051   0.0158
 -10.750   0.1469   0.07003   0.06670  -0.1643   0.8020   0.0161
 -10.500   0.1054   0.07485   0.07143  -0.1803   0.8140   0.0154
 -10.250   0.1078   0.07199   0.06854  -0.1810   0.8102   0.0156
 -10.000   0.1100   0.06898   0.06548  -0.1823   0.8066   0.0158
  -9.750   0.1052   0.06462   0.06115  -0.1849   0.8025   0.0158
  -9.500   0.0955   0.06032   0.05683  -0.1874   0.7983   0.0158
  -9.250   0.0880   0.05724   0.05368  -0.1884   0.7946   0.0160
  -9.000   0.0746   0.05404   0.05042  -0.1888   0.7908   0.0160
  -8.750   0.0610   0.05140   0.04775  -0.1879   0.7868   0.0160
  -8.500   0.0492   0.04944   0.04573  -0.1861   0.7829   0.0162
  -8.250   0.0399   0.04756   0.04374  -0.1842   0.7796   0.0163
  -8.000   0.0373   0.04549   0.04157  -0.1827   0.7764   0.0166
  -7.750   0.0373   0.04340   0.03940  -0.1812   0.7733   0.0169
  -7.500   0.0407   0.04128   0.03714  -0.1798   0.7705   0.0172
  -7.250   0.0472   0.03912   0.03483  -0.1784   0.7679   0.0179
  -7.000   0.0572   0.03690   0.03240  -0.1771   0.7656   0.0188
  -6.750   0.0736   0.03599   0.03105  -0.1748   0.7633   0.0200
  -6.500   0.0755   0.03175   0.02660  -0.1730   0.7609   0.0206
  -6.250   0.0911   0.02985   0.02466  -0.1726   0.7587   0.0211
  -6.000   0.1087   0.02834   0.02306  -0.1721   0.7564   0.0218
  -5.750   0.1282   0.02686   0.02143  -0.1716   0.7543   0.0228
  -5.500   0.1503   0.02549   0.01983  -0.1710   0.7523   0.0246
  -5.250   0.1752   0.02543   0.01932  -0.1699   0.7504   0.0266
  -5.000   0.1964   0.01926   0.01280  -0.1684   0.7488   0.0164
  -4.750   0.2215   0.01658   0.00974  -0.1664   0.7471   0.0114
  -4.500   0.2438   0.01552   0.00862  -0.1656   0.7453   0.0112
  -4.250   0.2656   0.01471   0.00775  -0.1647   0.7434   0.0112
  -4.000   0.2879   0.01410   0.00708  -0.1641   0.7416   0.0112
  -3.750   0.3094   0.01331   0.00624  -0.1636   0.7398   0.0119
  -3.500   0.3348   0.01290   0.00579  -0.1637   0.7383   0.0131
  -3.250   0.3615   0.01250   0.00534  -0.1641   0.7368   0.0180
  -3.000   0.3896   0.01223   0.00509  -0.1648   0.7353   0.0358
  -2.750   0.4154   0.01207   0.00500  -0.1650   0.7337   0.0525
  -2.500   0.4407   0.01184   0.00483  -0.1652   0.7319   0.0770
  -2.250   0.4646   0.00992   0.00456  -0.1671   0.7301   0.6201
  -2.000   0.4920   0.01015   0.00479  -0.1671   0.7286   0.6522
  -1.750   0.5196   0.01037   0.00498  -0.1672   0.7270   0.6678
  -1.500   0.5480   0.01058   0.00512  -0.1676   0.7256   0.6795
  -1.250   0.5757   0.01073   0.00529  -0.1677   0.7243   0.6866
  -1.000   0.6053   0.01092   0.00539  -0.1684   0.7231   0.6947
  -0.750   0.6334   0.01108   0.00556  -0.1686   0.7219   0.7004
  -0.500   0.6631   0.01127   0.00571  -0.1694   0.7207   0.7053
  -0.250   0.6899   0.01135   0.00576  -0.1697   0.7193   0.7079
   0.000   0.7161   0.01141   0.00580  -0.1699   0.7177   0.7100
   0.250   0.7422   0.01145   0.00585  -0.1700   0.7161   0.7116
   0.500   0.7688   0.01152   0.00592  -0.1703   0.7146   0.7133
   0.750   0.7959   0.01160   0.00601  -0.1706   0.7133   0.7150
   1.000   0.8237   0.01168   0.00609  -0.1711   0.7120   0.7170
   1.250   0.8521   0.01177   0.00617  -0.1717   0.7108   0.7193
   1.500   0.8812   0.01185   0.00625  -0.1725   0.7096   0.7218
   1.750   0.9110   0.01194   0.00631  -0.1735   0.7085   0.7242
   2.000   0.9416   0.01204   0.00638  -0.1746   0.7074   0.7263
   2.250   0.9717   0.01218   0.00653  -0.1756   0.7062   0.7281
   2.500   0.9959   0.01233   0.00675  -0.1754   0.7049   0.7300
   2.750   1.0192   0.01248   0.00697  -0.1750   0.7035   0.7323
   3.000   1.0433   0.01264   0.00718  -0.1748   0.7020   0.7347
   3.250   1.0682   0.01280   0.00738  -0.1748   0.7005   0.7375
   3.500   1.0941   0.01295   0.00757  -0.1750   0.6989   0.7403
   3.750   1.1202   0.01307   0.00773  -0.1752   0.6975   0.7426
   4.000   1.1468   0.01319   0.00792  -0.1755   0.6963   0.7448
   4.250   1.1747   0.01333   0.00812  -0.1760   0.6952   0.7471
   4.500   1.2039   0.01346   0.00828  -0.1769   0.6941   0.7496
   4.750   1.2343   0.01360   0.00846  -0.1780   0.6929   0.7524
   5.000   1.2652   0.01382   0.00872  -0.1792   0.6918   0.7552
   5.250   1.2848   0.01407   0.00907  -0.1782   0.6902   0.7579
   5.500   1.3011   0.01428   0.00941  -0.1764   0.6876   0.7606
   5.750   1.3251   0.01397   0.00915  -0.1758   0.6823   0.7635
   6.000   1.3540   0.01329   0.00844  -0.1759   0.6735   0.7666
   6.250   1.3760   0.01285   0.00799  -0.1748   0.6655   0.7699
   6.500   1.3942   0.01279   0.00798  -0.1731   0.6601   0.7729
   6.750   1.4048   0.01279   0.00810  -0.1699   0.6551   0.7758
   7.000   1.4269   0.01271   0.00807  -0.1691   0.6509   0.7790
   7.250   1.4413   0.01277   0.00820  -0.1668   0.6464   0.7829
   7.500   1.4443   0.01294   0.00846  -0.1622   0.6401   0.7871
   7.750   1.4660   0.01287   0.00843  -0.1612   0.6341   0.7902
   8.000   1.4619   0.01325   0.00896  -0.1555   0.6271   0.7944
   8.250   1.4732   0.01340   0.00914  -0.1527   0.6187   0.7986
   8.500   1.4735   0.01384   0.00968  -0.1480   0.6085   0.8029
   8.750   1.4761   0.01435   0.01028  -0.1439   0.5971   0.8071
   9.000   1.4755   0.01503   0.01100  -0.1393   0.5807   0.8121
   9.250   1.4687   0.01607   0.01201  -0.1340   0.5536   0.8173
   9.500   1.4512   0.01773   0.01352  -0.1272   0.5130   0.8223
   9.750   1.4241   0.02025   0.01581  -0.1195   0.4682   0.8281
  10.000   1.3940   0.02334   0.01867  -0.1121   0.4234   0.8334
  10.250   1.3710   0.02637   0.02151  -0.1062   0.3836   0.8388
  10.500   1.3476   0.02972   0.02463  -0.1008   0.3389   0.8448
  10.750   1.3317   0.03272   0.02746  -0.0965   0.2998   0.8504
  11.000   1.3175   0.03576   0.03029  -0.0927   0.2578   0.8568
  11.250   1.3113   0.03828   0.03267  -0.0899   0.2222   0.8633
  11.500   1.3071   0.04072   0.03496  -0.0874   0.1896   0.8709
  11.750   1.3058   0.04295   0.03707  -0.0852   0.1605   0.8794
  12.000   1.3068   0.04501   0.03905  -0.0834   0.1352   0.8905
  12.250   1.3091   0.04691   0.04091  -0.0815   0.1141   0.9096
  12.500   1.3134   0.04872   0.04271  -0.0802   0.0956   1.0000
  12.750   1.3192   0.05073   0.04463  -0.0793   0.0788   1.0000
  13.000   1.3258   0.05270   0.04654  -0.0784   0.0645   1.0000
  13.250   1.3321   0.05472   0.04847  -0.0776   0.0507   1.0000
  13.500   1.3388   0.05671   0.05042  -0.0768   0.0399   1.0000
  13.750   1.3444   0.05885   0.05250  -0.0760   0.0302   1.0000
  14.000   1.3518   0.06084   0.05447  -0.0754   0.0239   1.0000
  14.250   1.3582   0.06294   0.05659  -0.0747   0.0192   1.0000
  14.500   1.3632   0.06523   0.05889  -0.0739   0.0152   1.0000
  14.750   1.3689   0.06749   0.06116  -0.0733   0.0118   1.0000
  15.000   1.3753   0.06970   0.06344  -0.0728   0.0097   1.0000
  15.250   1.3777   0.07241   0.06620  -0.0721   0.0073   1.0000
  15.500   1.3766   0.07556   0.06942  -0.0713   0.0060   1.0000
  15.750   1.3821   0.07800   0.07197  -0.0710   0.0050   1.0000
  16.000   1.3845   0.08084   0.07489  -0.0706   0.0044   1.0000
  16.250   1.3804   0.08459   0.07875  -0.0701   0.0040   1.0000
  16.500   1.3831   0.08753   0.08181  -0.0700   0.0037   1.0000
  16.750   1.3846   0.09063   0.08503  -0.0699   0.0034   1.0000
  17.000   1.3850   0.09393   0.08844  -0.0699   0.0032   1.0000
  17.250   1.3852   0.09728   0.09189  -0.0700   0.0031   1.0000
  17.500   1.3845   0.10082   0.09553  -0.0703   0.0029   1.0000
  17.750   1.3815   0.10471   0.09952  -0.0706   0.0028   1.0000
  18.000   1.3765   0.10891   0.10384  -0.0711   0.0027   1.0000
  18.250   1.3698   0.11332   0.10836  -0.0716   0.0026   1.0000
<< Back to NREL's S831 Airfoil (s831-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S831 Airfoil (s831-nr)