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NREL's S801 Airfoil (s801-nr) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NREL's S801 Airfoil (s801-nr)
Reynolds number: 100,000
Max Cl/Cd: 52.1 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s801-nr-100000.txt
Download as CSV file: xf-s801-nr-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S801 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3984   0.11953   0.11513  -0.0389   1.0000   0.1070
  -9.500  -0.4301   0.11944   0.11518  -0.0375   1.0000   0.1076
  -9.250  -0.4598   0.11710   0.11295  -0.0436   0.9963   0.1082
  -9.000  -0.4042   0.11214   0.10788  -0.0357   0.9969   0.1129
  -8.750  -0.3951   0.10833   0.10407  -0.0411   0.9918   0.1205
  -8.500  -0.4288   0.10369   0.09953  -0.0552   0.9807   0.1229
  -8.250  -0.3699   0.09996   0.09570  -0.0483   0.9825   0.1302
  -8.000  -0.3913   0.09566   0.09147  -0.0587   0.9726   0.1374
  -7.750  -0.3846   0.09140   0.08723  -0.0593   0.9660   0.1404
  -7.500  -0.3562   0.08846   0.08425  -0.0591   0.9630   0.1469
  -7.250  -0.4241   0.08276   0.07838  -0.0755   0.9450   0.1536
  -6.750  -0.3745   0.07711   0.07293  -0.0690   0.9395   0.1641
  -6.500  -0.3690   0.07202   0.06777  -0.0746   0.9341   0.1738
  -6.250  -0.3761   0.06983   0.06554  -0.0737   0.9264   0.1808
  -6.000  -0.3772   0.05049   0.04450  -0.0894   0.9203   0.0956
  -5.750  -0.3543   0.04454   0.03776  -0.0906   0.9172   0.0778
  -5.500  -0.3394   0.04201   0.03489  -0.0899   0.9125   0.0771
  -5.250  -0.3118   0.03920   0.03162  -0.0911   0.9092   0.0764
  -5.000  -0.2784   0.03651   0.02845  -0.0929   0.9068   0.0750
  -4.750  -0.2427   0.03445   0.02593  -0.0946   0.9048   0.0750
  -4.500  -0.2194   0.03333   0.02451  -0.0942   0.9020   0.0765
  -4.250  -0.2018   0.03277   0.02369  -0.0927   0.8981   0.0792
  -4.000  -0.1762   0.03154   0.02243  -0.0927   0.8950   0.0828
  -3.750  -0.1462   0.03069   0.02157  -0.0933   0.8922   0.0874
  -3.500  -0.1138   0.02994   0.02073  -0.0941   0.8901   0.0944
  -3.250  -0.0830   0.02922   0.02016  -0.0951   0.8882   0.1097
  -3.000  -0.0733   0.02890   0.02003  -0.0928   0.8840   0.1294
  -2.750  -0.0450   0.02671   0.01940  -0.0947   0.8813   0.3740
  -2.500  -0.0402   0.02678   0.02080  -0.0890   0.8783   0.6476
  -2.250  -0.0254   0.02801   0.02198  -0.0849   0.8753   0.7433
  -2.000  -0.0188   0.02901   0.02293  -0.0792   0.8721   0.7861
  -1.750  -0.0258   0.02968   0.02359  -0.0724   0.8682   0.8099
  -1.500  -0.0236   0.03012   0.02397  -0.0669   0.8643   0.8352
  -1.250  -0.0175   0.03041   0.02418  -0.0620   0.8612   0.8620
  -1.000  -0.0076   0.03056   0.02424  -0.0575   0.8585   0.8895
  -0.750  -0.0135   0.03064   0.02429  -0.0515   0.8545   0.9104
  -0.500  -0.0102   0.03069   0.02428  -0.0473   0.8508   0.9333
  -0.250   0.0196   0.03085   0.02433  -0.0476   0.8471   0.9607
   0.000   0.1180   0.03162   0.02484  -0.0607   0.8442   0.9868
   0.250   0.1944   0.03224   0.02525  -0.0705   0.8416   1.0000
   0.500   0.1615   0.03257   0.02560  -0.0621   0.8350   1.0000
   0.750   0.1764   0.03284   0.02579  -0.0611   0.8303   1.0000
   1.000   0.2159   0.03323   0.02605  -0.0637   0.8268   1.0000
   1.250   0.2076   0.03380   0.02661  -0.0598   0.8197   1.0000
   1.500   0.2389   0.03427   0.02699  -0.0614   0.8145   1.0000
   1.750   0.2782   0.03479   0.02743  -0.0640   0.8101   1.0000
   2.000   0.2874   0.03550   0.02811  -0.0628   0.8020   1.0000
   2.250   0.3290   0.03594   0.02848  -0.0657   0.7972   1.0000
   2.500   0.3457   0.03672   0.02925  -0.0655   0.7890   1.0000
   2.750   0.3824   0.03717   0.02967  -0.0676   0.7828   1.0000
   3.000   0.4080   0.03788   0.03036  -0.0684   0.7752   1.0000
   3.250   0.4411   0.03833   0.03081  -0.0700   0.7678   1.0000
   3.500   0.4697   0.03895   0.03143  -0.0710   0.7597   1.0000
   3.750   0.5037   0.03934   0.03182  -0.0726   0.7520   1.0000
   4.000   0.5298   0.03999   0.03250  -0.0732   0.7428   1.0000
   4.250   0.5694   0.04013   0.03267  -0.0752   0.7358   1.0000
   4.500   0.5919   0.04082   0.03340  -0.0754   0.7251   1.0000
   4.750   0.6393   0.04052   0.03316  -0.0779   0.7193   1.0000
   5.000   0.6601   0.04118   0.03387  -0.0777   0.7073   1.0000
   5.250   0.7153   0.04025   0.03302  -0.0806   0.7029   1.0000
   5.500   0.7365   0.04073   0.03358  -0.0802   0.6901   1.0000
   5.750   0.7916   0.03939   0.03234  -0.0826   0.6852   1.0000
   6.000   0.8214   0.03915   0.03220  -0.0827   0.6735   1.0000
   6.250   0.8857   0.03663   0.02983  -0.0854   0.6701   1.0000
   6.500   0.9180   0.03583   0.02915  -0.0852   0.6581   1.0000
   6.750   0.9976   0.03184   0.02537  -0.0890   0.6565   1.0000
   7.000   1.0298   0.03079   0.02445  -0.0886   0.6436   1.0000
   7.250   1.0732   0.02895   0.02279  -0.0892   0.6316   1.0000
   7.500   1.1225   0.02669   0.02070  -0.0903   0.6180   1.0000
   7.750   1.1573   0.02517   0.01931  -0.0898   0.5994   1.0000
   8.000   1.1804   0.02426   0.01851  -0.0880   0.5760   1.0000
   8.250   1.1908   0.02408   0.01842  -0.0847   0.5446   1.0000
   8.500   1.2104   0.02352   0.01776  -0.0824   0.4968   1.0000
   8.750   1.2274   0.02356   0.01727  -0.0798   0.4238   1.0000
   9.000   1.2257   0.02507   0.01828  -0.0757   0.3596   1.0000
   9.250   1.2211   0.02700   0.01977  -0.0719   0.3084   1.0000
   9.500   1.2187   0.02903   0.02144  -0.0688   0.2662   1.0000
   9.750   1.2196   0.03105   0.02313  -0.0662   0.2332   1.0000
  10.000   1.2246   0.03294   0.02480  -0.0642   0.2060   1.0000
  10.250   1.2336   0.03475   0.02636  -0.0625   0.1846   1.0000
  10.500   1.2452   0.03643   0.02797  -0.0612   0.1664   1.0000
  10.750   1.2602   0.03804   0.02950  -0.0602   0.1515   1.0000
  11.000   1.2782   0.03960   0.03098  -0.0595   0.1389   1.0000
  11.250   1.3021   0.04113   0.03235  -0.0593   0.1276   1.0000
  11.500   1.3194   0.04269   0.03405  -0.0585   0.1190   1.0000
  11.750   1.3447   0.04440   0.03582  -0.0584   0.1107   1.0000
  12.000   1.3695   0.04603   0.03745  -0.0584   0.1038   1.0000
  12.250   1.3959   0.04819   0.03977  -0.0585   0.0977   1.0000
  12.500   1.4102   0.05013   0.04189  -0.0576   0.0929   1.0000
  12.750   1.4465   0.05285   0.04460  -0.0590   0.0875   1.0000
  13.000   1.4464   0.05525   0.04742  -0.0567   0.0848   1.0000
  13.250   1.4518   0.05771   0.05014  -0.0551   0.0816   1.0000
  13.500   1.4621   0.06014   0.05271  -0.0542   0.0786   1.0000
  13.750   1.4780   0.06397   0.05666  -0.0541   0.0754   1.0000
  14.000   1.4620   0.06716   0.06025  -0.0513   0.0743   1.0000
  14.250   1.4460   0.07085   0.06433  -0.0492   0.0731   1.0000
  14.500   1.4290   0.07497   0.06879  -0.0475   0.0721   1.0000
  14.750   1.4104   0.07954   0.07369  -0.0464   0.0713   1.0000
  15.000   1.3889   0.08460   0.07906  -0.0458   0.0707   1.0000
  15.250   1.3641   0.09027   0.08503  -0.0458   0.0704   1.0000
  15.500   1.3344   0.09683   0.09189  -0.0468   0.0706   1.0000
  15.750   1.2996   0.10458   0.09994  -0.0490   0.0712   1.0000
  16.000   1.2617   0.11362   0.10924  -0.0528   0.0723   1.0000
  16.250   1.2230   0.12396   0.11977  -0.0582   0.0735   1.0000
  16.500   1.1865   0.13547   0.13142  -0.0650   0.0747   1.0000
  16.750   1.1570   0.14728   0.14327  -0.0720   0.0757   1.0000
  17.000   0.8175   0.19849   0.19502  -0.0919   0.1428   1.0000
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