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NREL's S804 Airfoil (s804-nr) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NREL's S804 Airfoil (s804-nr)
Reynolds number: 50,000
Max Cl/Cd: 4.76 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s804-nr-50000.txt
Download as CSV file: xf-s804-nr-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S804 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2216   0.11579   0.11015  -0.0209   1.0000   0.3138
  -8.250  -0.2662   0.11905   0.11367  -0.0152   1.0000   0.3175
  -8.000  -0.3113   0.12211   0.11696  -0.0110   1.0000   0.3188
  -7.750  -0.2538   0.11462   0.10939  -0.0168   0.9917   0.3265
  -7.250  -0.4110   0.08325   0.07805  -0.0543   0.9630   0.1580
  -7.000  -0.4544   0.06748   0.06166  -0.0727   0.9468   0.1422
  -6.750  -0.4390   0.06030   0.05383  -0.0814   0.9326   0.1406
  -6.500  -0.4117   0.05482   0.04771  -0.0880   0.9190   0.1410
  -6.250  -0.3757   0.05032   0.04277  -0.0931   0.9064   0.1424
  -6.000  -0.3256   0.04732   0.03967  -0.0981   0.8954   0.1493
  -5.750  -0.2923   0.04450   0.03625  -0.1014   0.8809   0.1548
  -5.500  -0.2577   0.04232   0.03393  -0.1034   0.8676   0.1618
  -5.250  -0.2087   0.04001   0.03135  -0.1072   0.8569   0.1753
  -5.000  -0.1698   0.03832   0.02958  -0.1090   0.8445   0.1917
  -4.750  -0.1398   0.03712   0.02857  -0.1094   0.8316   0.2140
  -4.500  -0.0853   0.03473   0.02661  -0.1131   0.8236   0.2784
  -4.250  -0.0671   0.03463   0.02725  -0.1112   0.8091   0.3568
  -4.000  -0.0408   0.03710   0.03023  -0.1061   0.7982   0.4394
  -3.750  -0.0220   0.03931   0.03245  -0.1009   0.7860   0.4932
  -3.500  -0.0173   0.04139   0.03458  -0.0938   0.7735   0.5192
  -3.250   0.0092   0.04278   0.03586  -0.0889   0.7646   0.5587
  -3.000   0.0064   0.04413   0.03719  -0.0831   0.7522   0.5803
  -2.750   0.0276   0.04502   0.03799  -0.0777   0.7443   0.6091
  -2.500   0.0216   0.04605   0.03900  -0.0726   0.7332   0.6287
  -2.250   0.0391   0.04638   0.03918  -0.0695   0.7248   0.6572
  -2.000   0.0523   0.04673   0.03941  -0.0665   0.7170   0.6817
  -1.750   0.0314   0.04793   0.04066  -0.0604   0.7067   0.6925
  -1.500   0.0652   0.04763   0.04014  -0.0598   0.7015   0.7210
  -1.250   0.0314   0.04944   0.04205  -0.0539   0.6928   0.7278
  -1.000   0.0320   0.05019   0.04274  -0.0514   0.6857   0.7446
  -0.750   0.0595   0.04987   0.04225  -0.0497   0.6806   0.7657
  -0.500   0.0509   0.05139   0.04373  -0.0481   0.6746   0.7789
  -0.250   0.0381   0.05286   0.04522  -0.0451   0.6708   0.7898
   0.000   0.0392   0.05394   0.04625  -0.0437   0.6677   0.8030
   0.250   0.0478   0.05477   0.04700  -0.0429   0.6645   0.8169
   0.500   0.0694   0.05522   0.04732  -0.0429   0.6607   0.8318
   0.750   0.0909   0.05584   0.04781  -0.0428   0.6572   0.8455
   1.000   0.0908   0.05728   0.04922  -0.0420   0.6569   0.8560
   1.250   0.1036   0.05865   0.05053  -0.0426   0.6577   0.8677
   1.500   0.0448   0.06254   0.05466  -0.0414   0.6893   0.8722
   1.750   0.0702   0.06448   0.05650  -0.0436   0.6985   0.8854
   2.000  -0.0165   0.06816   0.06057  -0.0421   0.8231   0.8872
   2.250  -0.0097   0.06824   0.06059  -0.0414   0.8158   0.8990
   2.500   0.0161   0.06938   0.06164  -0.0431   0.8065   0.9138
   2.750   0.0482   0.07169   0.06385  -0.0460   0.8014   0.9301
   3.000   0.0621   0.07165   0.06380  -0.0465   0.7881   0.9445
   3.500   0.1183   0.07467   0.06671  -0.0534   0.7697   1.0000
   3.750   0.1672   0.07835   0.07022  -0.0602   0.7632   1.0000
   4.000   0.1773   0.07899   0.07080  -0.0613   0.7520   1.0000
   4.250   0.2204   0.08216   0.07385  -0.0670   0.7440   1.0000
   4.500   0.2450   0.08465   0.07625  -0.0704   0.7382   1.0000
   4.750   0.2691   0.08627   0.07780  -0.0732   0.7261   1.0000
   5.000   0.3221   0.09118   0.08257  -0.0800   0.7208   1.0000
   5.250   0.3204   0.09102   0.08240  -0.0796   0.7079   1.0000
   5.500   0.3638   0.09491   0.08618  -0.0848   0.7015   1.0000
   5.750   0.3712   0.09631   0.08754  -0.0857   0.6921   1.0000
   6.000   0.4048   0.09928   0.09043  -0.0894   0.6827   1.0000
   6.250   0.4538   0.10486   0.09588  -0.0950   0.6785   1.0000
   6.500   0.4430   0.10402   0.09506  -0.0934   0.6649   1.0000
   6.750   0.4856   0.10854   0.09949  -0.0977   0.6593   1.0000
   7.000   0.4809   0.10915   0.10008  -0.0970   0.6479   1.0000
   7.250   0.5140   0.11265   0.10351  -0.0998   0.6403   1.0000
   7.500   0.5279   0.11555   0.10637  -0.1011   0.6345   1.0000
   7.750   0.5401   0.11715   0.10795  -0.1017   0.6225   1.0000
   8.000   0.5822   0.12237   0.11310  -0.1049   0.6174   1.0000
   8.250   0.5679   0.12218   0.11293  -0.1036   0.6057   1.0000
   8.500   0.5991   0.12596   0.11668  -0.1056   0.5988   1.0000
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