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NREL's S821 Airfoil (s821-nr) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NREL's S821 Airfoil (s821-nr)
Reynolds number: 100,000
Max Cl/Cd: 37.4 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s821-nr-100000-n5.txt
Download as CSV file: xf-s821-nr-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S821 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.000  -0.0279   0.10296   0.09557  -0.0518   0.9504   0.2139
  -5.750  -0.0197   0.09904   0.09161  -0.0554   0.9441   0.2167
  -5.500  -0.0379   0.09315   0.08566  -0.0581   0.9319   0.2195
  -5.250  -0.0084   0.09144   0.08399  -0.0604   0.9260   0.2202
  -5.000   0.0091   0.09005   0.08267  -0.0603   0.9129   0.2209
  -4.750   0.0288   0.08821   0.08087  -0.0614   0.9028   0.2218
  -4.250   0.0667   0.08434   0.07706  -0.0638   0.8816   0.2248
  -3.750   0.0868   0.07754   0.07022  -0.0687   0.8615   0.2296
  -3.250   0.1052   0.06954   0.06213  -0.0753   0.8412   0.2340
  -2.250   0.1525   0.05494   0.04727  -0.0895   0.7934   0.2457
  -2.000  -0.0591   0.03189   0.02310  -0.0989   0.7681   0.2622
  -1.750  -0.0226   0.03162   0.02289  -0.1002   0.7584   0.2634
  -1.500   0.0069   0.03134   0.02266  -0.1006   0.7467   0.2647
  -1.250   0.0437   0.03087   0.02220  -0.1025   0.7372   0.2664
  -1.000   0.0671   0.03021   0.02152  -0.1030   0.7247   0.2685
  -0.750   0.1020   0.02906   0.02023  -0.1061   0.7151   0.2716
  -0.500   0.1237   0.02771   0.01870  -0.1077   0.7029   0.2749
  -0.250   0.1603   0.02658   0.01734  -0.1110   0.6938   0.2779
   0.000   0.1831   0.02646   0.01733  -0.1100   0.6819   0.2792
   0.250   0.2150   0.02628   0.01718  -0.1106   0.6721   0.2809
   0.500   0.2411   0.02610   0.01704  -0.1105   0.6616   0.2829
   0.750   0.2699   0.02582   0.01675  -0.1110   0.6519   0.2852
   1.000   0.3016   0.02544   0.01630  -0.1121   0.6430   0.2884
   1.250   0.3288   0.02496   0.01572  -0.1129   0.6323   0.2920
   1.500   0.3622   0.02461   0.01528  -0.1141   0.6238   0.2951
   1.750   0.3860   0.02464   0.01544  -0.1133   0.6141   0.2972
   2.000   0.4137   0.02461   0.01548  -0.1132   0.6052   0.2996
   2.250   0.4446   0.02452   0.01537  -0.1137   0.5973   0.3027
   2.500   0.4700   0.02437   0.01526  -0.1135   0.5876   0.3059
   2.750   0.5023   0.02411   0.01488  -0.1145   0.5795   0.3100
   3.000   0.5306   0.02404   0.01484  -0.1147   0.5714   0.3131
   3.250   0.5553   0.02413   0.01505  -0.1139   0.5626   0.3158
   3.500   0.5854   0.02418   0.01512  -0.1141   0.5550   0.3194
   3.750   0.6113   0.02422   0.01522  -0.1138   0.5465   0.3234
   4.000   0.6395   0.02415   0.01512  -0.1139   0.5376   0.3283
   4.250   0.6704   0.02414   0.01508  -0.1143   0.5297   0.3321
   4.500   0.6913   0.02427   0.01538  -0.1129   0.5196   0.3351
   4.750   0.7187   0.02433   0.01545  -0.1125   0.5106   0.3390
   5.000   0.7432   0.02441   0.01558  -0.1118   0.5009   0.3436
   5.250   0.7699   0.02441   0.01552  -0.1116   0.4907   0.3491
   5.500   0.7940   0.02453   0.01573  -0.1107   0.4811   0.3528
   5.750   0.8153   0.02468   0.01601  -0.1093   0.4706   0.3568
   6.000   0.8407   0.02480   0.01612  -0.1086   0.4609   0.3618
   6.250   0.8620   0.02492   0.01629  -0.1074   0.4497   0.3673
   6.500   0.8861   0.02503   0.01639  -0.1065   0.4394   0.3721
   6.750   0.9036   0.02525   0.01676  -0.1046   0.4277   0.3761
   7.000   0.9246   0.02544   0.01698  -0.1031   0.4169   0.3813
   7.250   0.9420   0.02563   0.01722  -0.1013   0.4048   0.3869
   7.500   0.9599   0.02583   0.01743  -0.0995   0.3931   0.3923
   7.750   0.9748   0.02610   0.01778  -0.0972   0.3808   0.3965
   8.000   0.9889   0.02646   0.01824  -0.0949   0.3678   0.4015
   8.250   1.0041   0.02685   0.01863  -0.0928   0.3544   0.4073
   8.500   1.0187   0.02731   0.01905  -0.0909   0.3395   0.4134
   8.750   1.0302   0.02785   0.01971  -0.0884   0.3238   0.4176
   9.000   1.0409   0.02849   0.02040  -0.0860   0.3072   0.4226
   9.250   1.0510   0.02923   0.02113  -0.0836   0.2896   0.4283
   9.500   1.0601   0.03009   0.02192  -0.0814   0.2714   0.4343
   9.750   1.0667   0.03109   0.02290  -0.0790   0.2537   0.4389
  10.000   1.0717   0.03225   0.02406  -0.0766   0.2371   0.4435
  10.250   1.0760   0.03358   0.02535  -0.0744   0.2217   0.4488
  10.500   1.0800   0.03506   0.02678  -0.0724   0.2078   0.4547
  11.000   1.0872   0.03833   0.03006  -0.0690   0.1834   0.4648
  11.250   1.0908   0.04012   0.03189  -0.0676   0.1730   0.4700
  11.500   1.0932   0.04212   0.03388  -0.0664   0.1639   0.4758
  11.750   1.0976   0.04413   0.03589  -0.0655   0.1549   0.4823
  12.000   1.1009   0.04623   0.03806  -0.0647   0.1471   0.4873
  12.250   1.1029   0.04853   0.04040  -0.0639   0.1401   0.4927
  12.500   1.1073   0.05077   0.04271  -0.0635   0.1331   0.4991
  12.750   1.1093   0.05334   0.04525  -0.0632   0.1273   0.5056
  13.000   1.1139   0.05571   0.04774  -0.0630   0.1210   0.5113
  13.250   1.1153   0.05843   0.05049  -0.0629   0.1161   0.5171
  13.500   1.1202   0.06097   0.05314  -0.0629   0.1106   0.5242
  13.750   1.1223   0.06389   0.05604  -0.0633   0.1061   0.5314
  14.000   1.1262   0.06660   0.05890  -0.0634   0.1013   0.5373
  14.250   1.1283   0.06959   0.06193  -0.0638   0.0973   0.5441
  14.500   1.1320   0.07255   0.06495  -0.0643   0.0932   0.5521
  14.750   1.1343   0.07566   0.06815  -0.0649   0.0894   0.5588
  15.000   1.1367   0.07880   0.07135  -0.0655   0.0861   0.5662
  15.250   1.1395   0.08204   0.07469  -0.0663   0.0824   0.5746
  15.500   1.1411   0.08537   0.07805  -0.0672   0.0797   0.5819
  15.750   1.1438   0.08871   0.08153  -0.0680   0.0764   0.5901
  16.000   1.1461   0.09217   0.08504  -0.0691   0.0736   0.5993
  16.250   1.1480   0.09561   0.08857  -0.0702   0.0711   0.6074
  16.500   1.1495   0.09926   0.09235  -0.0714   0.0684   0.6169
  16.750   1.1512   0.10285   0.09600  -0.0728   0.0661   0.6264
  17.000   1.1526   0.10657   0.09984  -0.0742   0.0639   0.6363
  17.250   1.1538   0.11038   0.10378  -0.0758   0.0616   0.6469
  17.500   1.1554   0.11403   0.10749  -0.0773   0.0597   0.6582
  17.750   1.1563   0.11790   0.11148  -0.0790   0.0578   0.6702
  18.000   1.1554   0.12213   0.11588  -0.0810   0.0559   0.6828
  18.250   1.1563   0.12593   0.11976  -0.0829   0.0543   0.6970
  18.500   1.1581   0.12958   0.12348  -0.0846   0.0528   0.7136
  18.750   1.1539   0.13447   0.12861  -0.0873   0.0511   0.7298
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