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NREL's S835 Airfoil (s835-nr) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NREL's S835 Airfoil (s835-nr)
Reynolds number: 100,000
Max Cl/Cd: 34.84 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s835-nr-100000.txt
Download as CSV file: xf-s835-nr-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S835 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4639   0.10993   0.10313  -0.0206   1.0000   0.3006
  -8.750  -0.4883   0.10511   0.09829  -0.0202   1.0000   0.3012
  -8.500  -1.0629   0.04507   0.03765  -0.0183   1.0000   0.3228
  -8.250  -1.0267   0.04694   0.03973  -0.0169   1.0000   0.3253
  -8.000  -0.9949   0.04863   0.04154  -0.0153   1.0000   0.3281
  -7.750  -0.9775   0.04892   0.04186  -0.0136   1.0000   0.3317
  -7.500  -1.0232   0.04094   0.03323  -0.0140   1.0000   0.3414
  -7.250  -1.0007   0.04162   0.03408  -0.0123   1.0000   0.3441
  -7.000  -0.9809   0.04209   0.03463  -0.0107   1.0000   0.3475
  -6.750  -0.9671   0.04152   0.03402  -0.0098   1.0000   0.3523
  -6.500  -0.9634   0.03818   0.03025  -0.0112   1.0000   0.3604
  -6.250  -0.9439   0.03858   0.03080  -0.0095   1.0000   0.3634
  -6.000  -0.9256   0.03880   0.03108  -0.0082   1.0000   0.3672
  -5.750  -0.9094   0.03817   0.03038  -0.0079   1.0000   0.3726
  -5.500  -0.8497   0.03799   0.02996  -0.0162   0.9841   0.3814
  -5.250  -0.8050   0.03913   0.03121  -0.0190   0.9731   0.3861
  -5.000  -0.7654   0.03922   0.03120  -0.0225   0.9657   0.3933
  -4.750  -0.7381   0.03804   0.02983  -0.0247   0.9564   0.4003
  -4.500  -0.6959   0.03913   0.03104  -0.0270   0.9505   0.4048
  -4.250  -0.6774   0.03873   0.03063  -0.0262   0.9429   0.4101
  -4.000  -0.6417   0.03785   0.02951  -0.0301   0.9373   0.4191
  -3.750  -0.6175   0.03816   0.02994  -0.0295   0.9295   0.4229
  -3.500  -0.5855   0.03847   0.03029  -0.0306   0.9234   0.4286
  -3.250  -0.5526   0.03766   0.02921  -0.0339   0.9178   0.4383
  -3.000  -0.5312   0.03792   0.02963  -0.0327   0.9106   0.4421
  -2.750  -0.4927   0.03846   0.03023  -0.0346   0.9054   0.4479
  -2.500  -0.4721   0.03781   0.02942  -0.0352   0.8981   0.4564
  -2.250  -0.4426   0.03796   0.02965  -0.0359   0.8920   0.4619
  -2.000  -0.4001   0.03865   0.03043  -0.0382   0.8877   0.4682
  -1.750  -0.3880   0.03807   0.02973  -0.0373   0.8789   0.4761
  -1.500  -0.3539   0.03822   0.02994  -0.0387   0.8735   0.4824
  -1.250  -0.3268   0.03868   0.03048  -0.0386   0.8671   0.4881
  -1.000  -0.3024   0.03841   0.03011  -0.0395   0.8596   0.4976
  -0.750  -0.2664   0.03871   0.03050  -0.0409   0.8548   0.5035
  -0.500  -0.2465   0.03906   0.03093  -0.0398   0.8472   0.5091
  -0.250  -0.2162   0.03882   0.03057  -0.0418   0.8402   0.5197
   0.000  -0.1794   0.03925   0.03114  -0.0427   0.8356   0.5251
   0.250  -0.1662   0.03965   0.03162  -0.0408   0.8267   0.5310
   0.500  -0.1313   0.03944   0.03131  -0.0433   0.8202   0.5419
   0.750  -0.0928   0.03983   0.03186  -0.0442   0.8160   0.5472
   1.000  -0.0853   0.04027   0.03236  -0.0416   0.8055   0.5533
   1.250  -0.0465   0.04013   0.03217  -0.0442   0.7996   0.5641
   1.500  -0.0054   0.04039   0.03258  -0.0453   0.7959   0.5700
   1.750  -0.0025   0.04089   0.03313  -0.0424   0.7835   0.5765
   2.000   0.0407   0.04068   0.03292  -0.0451   0.7786   0.5867
   2.250   0.0548   0.04123   0.03358  -0.0430   0.7690   0.5919
   2.500   0.0853   0.04131   0.03371  -0.0435   0.7613   0.6007
   2.750   0.1315   0.04097   0.03342  -0.0459   0.7572   0.6099
   3.000   0.1353   0.04171   0.03426  -0.0427   0.7444   0.6153
   3.250   0.1803   0.04131   0.03387  -0.0454   0.7391   0.6265
   3.500   0.2261   0.04082   0.03351  -0.0466   0.7359   0.6337
   3.750   0.2254   0.04167   0.03445  -0.0431   0.7209   0.6398
   4.000   0.2787   0.04080   0.03360  -0.0465   0.7172   0.6514
   4.250   0.2812   0.04160   0.03451  -0.0430   0.7031   0.6563
   4.500   0.3253   0.04082   0.03383  -0.0440   0.6984   0.6654
   4.750   0.3812   0.03944   0.03253  -0.0467   0.6959   0.6756
   5.500   0.4864   0.03702   0.03041  -0.0463   0.6741   0.7006
   6.250   0.5658   0.03528   0.02897  -0.0429   0.6421   0.7258
   6.500   0.6378   0.03249   0.02626  -0.0470   0.6388   0.7378
   6.750   0.7126   0.02952   0.02341  -0.0505   0.6350   0.7461
   7.000   0.7319   0.02926   0.02322  -0.0489   0.6185   0.7562
   7.250   0.7593   0.02844   0.02248  -0.0474   0.6036   0.7638
   7.500   0.8022   0.02722   0.02130  -0.0482   0.5873   0.7737
   7.750   0.8318   0.02648   0.02057  -0.0473   0.5679   0.7826
   8.000   0.8512   0.02611   0.02021  -0.0451   0.5463   0.7918
   8.250   0.8689   0.02589   0.01998  -0.0429   0.5219   0.8011
   8.500   0.8837   0.02572   0.01975  -0.0400   0.4967   0.8104
   8.750   0.8978   0.02577   0.01970  -0.0375   0.4688   0.8202
   9.000   0.9026   0.02606   0.01993  -0.0337   0.4407   0.8299
   9.250   0.9127   0.02637   0.02005  -0.0307   0.4115   0.8398
   9.500   0.9148   0.02699   0.02060  -0.0271   0.3825   0.8507
   9.750   0.9178   0.02755   0.02101  -0.0234   0.3556   0.8610
  10.000   0.9222   0.02836   0.02167  -0.0204   0.3285   0.8725
  10.250   0.9235   0.02916   0.02237  -0.0169   0.3039   0.8847
  10.500   0.9248   0.02996   0.02306  -0.0135   0.2813   0.8977
  10.750   0.9265   0.03082   0.02379  -0.0104   0.2603   0.9123
  11.000   0.9287   0.03168   0.02455  -0.0074   0.2408   0.9292
  11.250   0.9341   0.03261   0.02538  -0.0053   0.2217   0.9511
  11.500   0.9447   0.03377   0.02652  -0.0050   0.2013   1.0000
  11.750   0.9593   0.03551   0.02817  -0.0056   0.1821   1.0000
  12.000   0.9742   0.03729   0.02983  -0.0062   0.1651   1.0000
  12.250   0.9897   0.03909   0.03152  -0.0068   0.1500   1.0000
  12.500   1.0059   0.04091   0.03323  -0.0074   0.1369   1.0000
  12.750   1.0223   0.04274   0.03499  -0.0079   0.1254   1.0000
  13.000   1.0393   0.04458   0.03676  -0.0084   0.1154   1.0000
  13.250   1.0580   0.04637   0.03846  -0.0089   0.1068   1.0000
  13.500   1.0793   0.04803   0.03995  -0.0095   0.0992   1.0000
  13.750   1.0926   0.05000   0.04202  -0.0096   0.0930   1.0000
  14.000   1.1093   0.05199   0.04403  -0.0098   0.0873   1.0000
  14.250   1.1356   0.05354   0.04539  -0.0105   0.0821   1.0000
  14.500   1.1412   0.05601   0.04810  -0.0100   0.0783   1.0000
  14.750   1.1645   0.05771   0.04966  -0.0105   0.0743   1.0000
  15.000   1.1664   0.06048   0.05271  -0.0099   0.0716   1.0000
  15.250   1.1878   0.06228   0.05441  -0.0102   0.0686   1.0000
  15.500   1.1907   0.06538   0.05775  -0.0099   0.0667   1.0000
  15.750   1.1860   0.06879   0.06143  -0.0094   0.0650   1.0000
  16.000   1.1945   0.07128   0.06398  -0.0094   0.0630   1.0000
  16.250   1.2090   0.07371   0.06637  -0.0097   0.0611   1.0000
  16.500   1.1886   0.07837   0.07141  -0.0096   0.0605   1.0000
  16.750   1.1683   0.08343   0.07681  -0.0101   0.0598   1.0000
  17.000   1.1467   0.08894   0.08263  -0.0113   0.0593   1.0000
  17.250   1.1224   0.09515   0.08914  -0.0132   0.0591   1.0000
  17.500   1.0916   0.10258   0.09689  -0.0163   0.0591   1.0000
  17.750   1.0537   0.11167   0.10632  -0.0209   0.0595   1.0000
  18.000   1.0099   0.12267   0.11761  -0.0275   0.0602   1.0000
  18.250   0.9671   0.13488   0.13006  -0.0353   0.0611   1.0000
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