Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NREL's S829 Airfoil (s829-nr) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NREL's S829 Airfoil (s829-nr)
Reynolds number: 200,000
Max Cl/Cd: 35.63 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s829-nr-200000-n5.txt
Download as CSV file: xf-s829-nr-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S829 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.4867   0.08341   0.07981  -0.0764   0.9137   0.0080
 -14.250  -0.5953   0.07608   0.07213  -0.0852   0.9579   0.0076
 -14.000  -0.6101   0.06940   0.06526  -0.0899   0.9489   0.0075
 -13.750  -0.6302   0.06317   0.05877  -0.0930   0.9402   0.0075
 -13.500  -0.6464   0.05851   0.05387  -0.0941   0.9317   0.0075
 -13.250  -0.6602   0.05473   0.04986  -0.0940   0.9241   0.0074
 -13.000  -0.6781   0.05079   0.04560  -0.0928   0.9169   0.0075
 -12.750  -0.6884   0.04782   0.04238  -0.0912   0.9104   0.0075
 -12.500  -0.6957   0.04524   0.03954  -0.0893   0.9044   0.0075
 -12.250  -0.7025   0.04260   0.03660  -0.0869   0.8994   0.0075
 -12.000  -0.7062   0.04004   0.03377  -0.0846   0.8943   0.0076
 -11.750  -0.7068   0.03760   0.03105  -0.0823   0.8902   0.0077
 -11.500  -0.7031   0.03547   0.02866  -0.0803   0.8867   0.0079
 -11.250  -0.6952   0.03370   0.02670  -0.0787   0.8828   0.0081
 -11.000  -0.6851   0.03225   0.02508  -0.0771   0.8793   0.0084
 -10.750  -0.6738   0.03091   0.02358  -0.0755   0.8761   0.0088
 -10.500  -0.6602   0.02971   0.02216  -0.0741   0.8735   0.0089
 -10.250  -0.6454   0.02849   0.02081  -0.0729   0.8701   0.0094
 -10.000  -0.6302   0.02736   0.01953  -0.0716   0.8668   0.0103
  -9.750  -0.6152   0.02628   0.01828  -0.0702   0.8640   0.0110
  -9.500  -0.6003   0.02535   0.01720  -0.0688   0.8616   0.0115
  -9.250  -0.5869   0.02433   0.01610  -0.0672   0.8594   0.0131
  -9.000  -0.5678   0.02378   0.01551  -0.0665   0.8567   0.0164
  -8.750  -0.5528   0.02291   0.01453  -0.0651   0.8540   0.0185
  -8.500  -0.5370   0.02214   0.01373  -0.0637   0.8515   0.0221
  -8.250  -0.5197   0.02153   0.01300  -0.0625   0.8493   0.0268
  -8.000  -0.5031   0.02090   0.01236  -0.0612   0.8473   0.0339
  -7.750  -0.4865   0.02029   0.01172  -0.0598   0.8453   0.0419
  -7.500  -0.4687   0.01976   0.01117  -0.0587   0.8425   0.0511
  -7.250  -0.4514   0.01924   0.01068  -0.0575   0.8401   0.0639
  -7.000  -0.4342   0.01873   0.01021  -0.0562   0.8379   0.0799
  -6.750  -0.4174   0.01823   0.00977  -0.0549   0.8359   0.1021
  -6.500  -0.4020   0.01767   0.00934  -0.0533   0.8341   0.1324
  -6.250  -0.3883   0.01708   0.00887  -0.0514   0.8324   0.1732
  -6.000  -0.3760   0.01650   0.00850  -0.0493   0.8303   0.2212
  -5.750  -0.3675   0.01588   0.00815  -0.0466   0.8276   0.2804
  -5.500  -0.3644   0.01517   0.00776  -0.0427   0.8247   0.3505
  -5.250  -0.3659   0.01445   0.00738  -0.0377   0.8220   0.4252
  -5.000  -0.3717   0.01378   0.00713  -0.0315   0.8197   0.5133
  -4.750  -0.2901   0.01499   0.00914  -0.0398   0.8206   0.6888
  -4.500  -0.2672   0.01532   0.00940  -0.0385   0.8193   0.7178
  -4.250  -0.2525   0.01534   0.00934  -0.0361   0.8179   0.7368
  -4.000  -0.2372   0.01557   0.00952  -0.0338   0.8154   0.7512
  -3.750  -0.2252   0.01579   0.00969  -0.0309   0.8129   0.7644
  -3.500  -0.2182   0.01599   0.00983  -0.0269   0.8103   0.7769
  -3.250  -0.1679   0.01688   0.01061  -0.0306   0.8097   0.7814
  -3.000  -0.1539   0.01713   0.01080  -0.0278   0.8077   0.7920
  -2.500  -0.0946   0.01800   0.01152  -0.0281   0.8057   0.8051
  -2.250  -0.0532   0.01837   0.01181  -0.0307   0.8051   0.8067
  -1.750  -0.0242   0.01859   0.01198  -0.0263   0.8007   0.8185
  -1.500   0.0087   0.01879   0.01215  -0.0276   0.7989   0.8197
  -1.250   0.0395   0.01895   0.01228  -0.0286   0.7974   0.8212
  -0.750   0.0579   0.01890   0.01219  -0.0221   0.7932   0.8324
  -0.500   0.0903   0.01895   0.01222  -0.0233   0.7922   0.8334
  -0.250   0.1218   0.01898   0.01223  -0.0244   0.7912   0.8345
   0.250   0.1375   0.01934   0.01263  -0.0177   0.7849   0.8437
   0.500   0.1495   0.01939   0.01269  -0.0151   0.7820   0.8471
   0.750   0.1767   0.01950   0.01280  -0.0154   0.7804   0.8484
   1.000   0.2033   0.01952   0.01284  -0.0155   0.7790   0.8499
   1.250   0.2293   0.01950   0.01284  -0.0155   0.7778   0.8516
   1.500   0.2514   0.01942   0.01277  -0.0147   0.7766   0.8544
   2.000   0.2498   0.01988   0.01331  -0.0047   0.7662   0.8631
   2.250   0.2772   0.01983   0.01329  -0.0049   0.7647   0.8646
   2.500   0.3042   0.01971   0.01322  -0.0050   0.7634   0.8662
   3.000   0.3000   0.01992   0.01351   0.0057   0.7518   0.8756
   3.250   0.3340   0.01970   0.01333   0.0044   0.7504   0.8763
   3.500   0.3584   0.01955   0.01327   0.0049   0.7465   0.8778
   3.750   0.3686   0.01942   0.01319   0.0082   0.7386   0.8809
   4.000   0.4321   0.01820   0.01201   0.0022   0.7354   0.8795
   4.250   0.4043   0.01818   0.01202   0.0126   0.7249   0.8876
   4.500   0.4345   0.01762   0.01152   0.0125   0.7172   0.8884
   4.750   0.4667   0.01699   0.01098   0.0120   0.7085   0.8892
   5.000   0.4566   0.01715   0.01121   0.0191   0.6973   0.8934
   5.250   0.4463   0.01723   0.01134   0.0260   0.6858   0.8994
   5.500   0.4493   0.01734   0.01151   0.0303   0.6729   0.9029
   5.750   0.4579   0.01757   0.01182   0.0333   0.6575   0.9056
   6.000   0.4735   0.01748   0.01180   0.0354   0.6390   0.9085
   6.250   0.4956   0.01704   0.01138   0.0368   0.6072   0.9112
   6.500   0.5554   0.01559   0.00919   0.0332   0.4755   0.9093
   6.750   0.5424   0.01625   0.00949   0.0400   0.4131   0.9153
   7.000   0.5382   0.01719   0.01015   0.0448   0.3524   0.9187
   7.250   0.5352   0.01812   0.01082   0.0492   0.2965   0.9229
   7.500   0.5357   0.01887   0.01137   0.0529   0.2524   0.9279
   7.750   0.5418   0.01972   0.01202   0.0556   0.2075   0.9312
   8.000   0.5511   0.02055   0.01268   0.0575   0.1674   0.9342
   8.250   0.5621   0.02127   0.01328   0.0593   0.1372   0.9376
   8.500   0.5729   0.02191   0.01386   0.0612   0.1147   0.9415
   8.750   0.5874   0.02262   0.01450   0.0623   0.0942   0.9443
   9.000   0.6047   0.02335   0.01520   0.0629   0.0798   0.9470
   9.250   0.6215   0.02406   0.01592   0.0636   0.0680   0.9501
   9.500   0.6372   0.02474   0.01662   0.0645   0.0580   0.9538
   9.750   0.6534   0.02549   0.01739   0.0652   0.0506   0.9570
  10.000   0.6728   0.02636   0.01829   0.0651   0.0440   0.9591
  10.250   0.6919   0.02722   0.01926   0.0651   0.0381   0.9615
  10.500   0.7098   0.02813   0.02022   0.0652   0.0336   0.9643
  10.750   0.7243   0.02920   0.02135   0.0659   0.0301   0.9680
  11.000   0.7439   0.03014   0.02242   0.0656   0.0270   0.9706
  11.250   0.7636   0.03124   0.02357   0.0651   0.0231   0.9726
  11.500   0.7790   0.03267   0.02509   0.0651   0.0209   0.9751
  11.750   0.7993   0.03361   0.02616   0.0647   0.0180   0.9777
  12.000   0.8156   0.03479   0.02743   0.0645   0.0160   0.9808
  12.250   0.8276   0.03655   0.02926   0.0646   0.0143   0.9833
  12.500   0.8464   0.03785   0.03079   0.0640   0.0127   0.9852
  12.750   0.8639   0.03916   0.03222   0.0633   0.0110   0.9875
  13.000   0.8770   0.04081   0.03398   0.0629   0.0100   0.9905
  13.250   0.8846   0.04300   0.03630   0.0630   0.0094   0.9942
  13.500   0.8936   0.04538   0.03891   0.0631   0.0086   0.9992
  13.750   0.8902   0.04702   0.04070   0.0656   0.0083   1.0000
  14.000   0.8857   0.04871   0.04253   0.0681   0.0080   1.0000
  14.250   0.8821   0.05084   0.04482   0.0700   0.0080   1.0000
  14.500   0.8782   0.05328   0.04743   0.0714   0.0075   1.0000
  14.750   0.8786   0.05528   0.04955   0.0720   0.0070   1.0000
  15.000   0.8677   0.05912   0.05364   0.0729   0.0072   1.0000
  15.250   0.8643   0.06190   0.05652   0.0729   0.0067   1.0000
  15.500   0.8576   0.06541   0.06019   0.0726   0.0065   1.0000
  15.750   0.8518   0.06895   0.06384   0.0719   0.0063   1.0000
  16.000   0.8338   0.07470   0.06988   0.0708   0.0066   1.0000
  16.250   0.8270   0.07894   0.07423   0.0690   0.0063   1.0000
  16.500   0.8086   0.08547   0.08095   0.0663   0.0063   1.0000
  16.750   0.7985   0.09099   0.08654   0.0630   0.0056   1.0000
  17.000   0.7537   0.10420   0.10025   0.0570   0.0067   1.0000
  17.250   0.7249   0.11530   0.11154   0.0508   0.0067   1.0000
<< Back to NREL's S829 Airfoil (s829-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S829 Airfoil (s829-nr)