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NREL's S831 Airfoil (s831-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NREL's S831 Airfoil (s831-nr)
Reynolds number: 1,000,000
Max Cl/Cd: 147.47 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s831-nr-1000000-n5.txt
Download as CSV file: xf-s831-nr-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750   0.1113   0.09292   0.08991  -0.1528   0.7477   0.0058
 -12.500   0.1143   0.08944   0.08643  -0.1541   0.7458   0.0059
 -12.250   0.1178   0.08623   0.08321  -0.1552   0.7436   0.0059
 -12.000   0.1254   0.08408   0.08106  -0.1561   0.7413   0.0061
 -11.750   0.1302   0.08129   0.07826  -0.1571   0.7390   0.0063
 -11.500   0.1326   0.07784   0.07480  -0.1584   0.7370   0.0063
 -11.000   0.1382   0.07136   0.06831  -0.1607   0.7332   0.0068
 -10.750   0.1374   0.06733   0.06429  -0.1620   0.7314   0.0066
 -10.500   0.1393   0.06399   0.06096  -0.1632   0.7294   0.0071
 -10.250   0.1376   0.05991   0.05689  -0.1647   0.7274   0.0070
 -10.000   0.1345   0.05569   0.05267  -0.1663   0.7253   0.0069
  -9.750   0.1307   0.05138   0.04836  -0.1682   0.7233   0.0075
  -9.500   0.1227   0.04643   0.04342  -0.1710   0.7211   0.0072
  -7.000  -0.0129   0.01864   0.01350  -0.1632   0.7043   0.0036
  -6.750   0.0053   0.01643   0.01097  -0.1620   0.7026   0.0035
  -6.500   0.0267   0.01515   0.00948  -0.1613   0.7009   0.0035
  -6.250   0.0490   0.01423   0.00840  -0.1607   0.6991   0.0035
  -6.000   0.0712   0.01346   0.00750  -0.1601   0.6972   0.0035
  -5.750   0.0934   0.01283   0.00677  -0.1595   0.6954   0.0035
  -5.500   0.1160   0.01233   0.00618  -0.1590   0.6935   0.0035
  -5.000   0.1625   0.01142   0.00514  -0.1584   0.6905   0.0035
  -4.750   0.1872   0.01104   0.00471  -0.1583   0.6891   0.0035
  -4.500   0.2124   0.01072   0.00435  -0.1583   0.6877   0.0036
  -4.250   0.2381   0.01043   0.00401  -0.1585   0.6862   0.0036
  -4.000   0.2642   0.01018   0.00373  -0.1586   0.6847   0.0036
  -3.750   0.2905   0.00994   0.00344  -0.1589   0.6832   0.0038
  -3.500   0.3171   0.00974   0.00320  -0.1591   0.6817   0.0039
  -3.250   0.3439   0.00956   0.00298  -0.1594   0.6803   0.0046
  -3.000   0.3708   0.00942   0.00282  -0.1597   0.6789   0.0060
  -2.500   0.4255   0.00914   0.00260  -0.1605   0.6762   0.0233
  -2.250   0.4532   0.00903   0.00252  -0.1610   0.6749   0.0309
  -2.000   0.4810   0.00893   0.00246  -0.1615   0.6736   0.0423
  -1.750   0.5088   0.00875   0.00239  -0.1621   0.6723   0.0796
  -1.500   0.5400   0.00703   0.00208  -0.1652   0.6711   0.5827
  -1.250   0.5682   0.00704   0.00209  -0.1656   0.6698   0.6044
  -1.000   0.5963   0.00706   0.00211  -0.1661   0.6685   0.6177
  -0.750   0.6242   0.00709   0.00213  -0.1665   0.6673   0.6249
  -0.500   0.6521   0.00714   0.00216  -0.1669   0.6661   0.6347
  -0.250   0.6798   0.00718   0.00219  -0.1672   0.6648   0.6395
   0.000   0.7078   0.00724   0.00222  -0.1676   0.6636   0.6447
   0.250   0.7358   0.00730   0.00225  -0.1681   0.6624   0.6471
   0.500   0.7635   0.00733   0.00227  -0.1685   0.6614   0.6487
   0.750   0.7909   0.00735   0.00231  -0.1688   0.6602   0.6506
   1.000   0.8183   0.00739   0.00235  -0.1692   0.6589   0.6526
   1.250   0.8457   0.00742   0.00240  -0.1695   0.6578   0.6546
   1.500   0.8729   0.00747   0.00246  -0.1698   0.6566   0.6566
   1.750   0.9001   0.00751   0.00251  -0.1701   0.6554   0.6586
   2.000   0.9270   0.00757   0.00257  -0.1704   0.6542   0.6606
   2.250   0.9536   0.00762   0.00263  -0.1705   0.6531   0.6625
   2.750   1.0063   0.00774   0.00277  -0.1708   0.6506   0.6662
   3.000   1.0331   0.00781   0.00285  -0.1711   0.6493   0.6682
   3.250   1.0599   0.00788   0.00294  -0.1713   0.6481   0.6705
   3.500   1.0852   0.00793   0.00304  -0.1713   0.6471   0.6729
   3.750   1.1108   0.00799   0.00314  -0.1713   0.6461   0.6753
   4.000   1.1362   0.00806   0.00324  -0.1713   0.6449   0.6775
   4.250   1.1615   0.00813   0.00336  -0.1712   0.6437   0.6795
   4.500   1.1866   0.00820   0.00348  -0.1711   0.6423   0.6816
   4.750   1.2116   0.00828   0.00361  -0.1710   0.6409   0.6838
   5.000   1.2343   0.00837   0.00374  -0.1704   0.6382   0.6862
   5.250   1.2502   0.00849   0.00387  -0.1684   0.6314   0.6887
   5.500   1.2616   0.00865   0.00403  -0.1654   0.6207   0.6914
   5.750   1.2741   0.00886   0.00424  -0.1627   0.6082   0.6940
   6.000   1.2892   0.00909   0.00448  -0.1606   0.5965   0.6965
   6.250   1.3042   0.00935   0.00476  -0.1586   0.5855   0.6992
   6.500   1.3183   0.00967   0.00508  -0.1564   0.5728   0.7020
   6.750   1.3290   0.01010   0.00549  -0.1537   0.5564   0.7048
   7.000   1.3302   0.01084   0.00614  -0.1492   0.5297   0.7076
   7.250   1.3171   0.01217   0.00728  -0.1424   0.4892   0.7103
   7.500   1.2971   0.01398   0.00889  -0.1348   0.4443   0.7132
   7.750   1.2828   0.01582   0.01056  -0.1286   0.4057   0.7165
   8.000   1.2691   0.01783   0.01240  -0.1229   0.3652   0.7199
   8.250   1.2551   0.02005   0.01443  -0.1175   0.3239   0.7230
   8.500   1.2524   0.02178   0.01605  -0.1140   0.2954   0.7258
   8.750   1.2455   0.02384   0.01796  -0.1100   0.2599   0.7286
   9.000   1.2422   0.02579   0.01977  -0.1067   0.2285   0.7315
   9.250   1.2423   0.02759   0.02146  -0.1040   0.2007   0.7346
   9.500   1.2444   0.02931   0.02307  -0.1015   0.1742   0.7379
  10.000   1.2485   0.03292   0.02646  -0.0970   0.1220   0.7438
  10.250   1.2555   0.03443   0.02791  -0.0954   0.1053   0.7472
  10.500   1.2629   0.03594   0.02936  -0.0939   0.0888   0.7506
  10.750   1.2728   0.03731   0.03070  -0.0927   0.0781   0.7538
  11.250   1.2909   0.04022   0.03355  -0.0902   0.0551   0.7599
  11.500   1.2987   0.04180   0.03509  -0.0890   0.0419   0.7634
  11.750   1.3086   0.04325   0.03651  -0.0879   0.0341   0.7673
  12.000   1.3167   0.04487   0.03810  -0.0868   0.0253   0.7708
  12.250   1.3263   0.04639   0.03961  -0.0858   0.0188   0.7744
  12.500   1.3361   0.04791   0.04114  -0.0849   0.0142   0.7783
  12.750   1.3457   0.04948   0.04272  -0.0840   0.0106   0.7822
  13.000   1.3573   0.05088   0.04416  -0.0834   0.0089   0.7859
  13.250   1.3686   0.05231   0.04564  -0.0827   0.0074   0.7897
  13.500   1.3784   0.05392   0.04729  -0.0820   0.0059   0.7941
  13.750   1.3890   0.05547   0.04889  -0.0813   0.0046   0.7988
  14.000   1.3996   0.05703   0.05049  -0.0807   0.0036   0.8033
  14.250   1.4099   0.05864   0.05218  -0.0802   0.0030   0.8084
  14.500   1.4194   0.06036   0.05396  -0.0796   0.0023   0.8137
  14.750   1.4277   0.06218   0.05583  -0.0790   0.0014   0.8185
  15.000   1.4369   0.06395   0.05768  -0.0784   0.0012   0.8243
  15.250   1.4450   0.06589   0.05970  -0.0779   0.0009   0.8303
  15.500   1.4535   0.06778   0.06167  -0.0774   0.0008   0.8368
  15.750   1.4612   0.06979   0.06377  -0.0770   0.0007   0.8447
  16.000   1.4689   0.07181   0.06589  -0.0766   0.0006   0.8539
  16.250   1.4765   0.07382   0.06802  -0.0761   0.0006   0.8655
  16.500   1.4823   0.07600   0.07033  -0.0757   0.0005   0.8832
  16.750   1.4856   0.07797   0.07252  -0.0747   0.0005   1.0000
  17.000   1.4916   0.08031   0.07494  -0.0745   0.0004   1.0000
  17.250   1.4968   0.08279   0.07750  -0.0743   0.0004   1.0000
  17.500   1.5015   0.08534   0.08013  -0.0742   0.0004   1.0000
  17.750   1.5040   0.08823   0.08312  -0.0741   0.0003   1.0000
  18.000   1.5063   0.09114   0.08613  -0.0741   0.0003   1.0000
  18.250   1.5064   0.09440   0.08949  -0.0741   0.0003   1.0000
  18.500   1.5073   0.09760   0.09280  -0.0743   0.0003   1.0000
  18.750   1.5087   0.10075   0.09604  -0.0746   0.0003   1.0000
  19.000   1.5046   0.10475   0.10017  -0.0750   0.0003   1.0000
  19.250   1.5042   0.10825   0.10377  -0.0756   0.0003   1.0000
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