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 S832 Airfoil (s832-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NREL's S832 Airfoil (s832-nr)
Reynolds number: 1,000,000
Max Cl/Cd: 163.33 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s832-nr-1000000.txt
Download as CSV file: xf-s832-nr-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S832 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.0373   0.08974   0.08706  -0.1105   0.7641   0.0065
 -10.750   0.0422   0.08663   0.08393  -0.1117   0.7619   0.0065
 -10.500   0.0030   0.09392   0.09107  -0.1227   0.7746   0.0062
 -10.250   0.0088   0.09106   0.08822  -0.1240   0.7718   0.0062
 -10.000   0.0140   0.08815   0.08531  -0.1252   0.7689   0.0062
  -9.750   0.0188   0.08522   0.08238  -0.1264   0.7659   0.0064
  -9.500   0.0229   0.08224   0.07937  -0.1276   0.7629   0.0066
  -9.250   0.0271   0.07921   0.07636  -0.1290   0.7603   0.0067
  -9.000   0.0290   0.07574   0.07291  -0.1308   0.7574   0.0069
  -8.750   0.0313   0.07263   0.06980  -0.1324   0.7544   0.0069
  -8.500   0.0327   0.06942   0.06660  -0.1341   0.7513   0.0070
  -8.250   0.0315   0.06579   0.06296  -0.1365   0.7480   0.0070
  -8.000   0.0275   0.06236   0.05955  -0.1392   0.7454   0.0070
  -7.750   0.0195   0.05943   0.05663  -0.1399   0.7422   0.0070
  -7.500   0.0155   0.05648   0.05363  -0.1400   0.7393   0.0070
  -7.250   0.0171   0.05335   0.05043  -0.1404   0.7364   0.0071
  -7.000   0.0213   0.05031   0.04730  -0.1405   0.7335   0.0071
  -6.750   0.0281   0.04734   0.04426  -0.1404   0.7312   0.0071
  -6.500   0.0361   0.04408   0.04091  -0.1399   0.7287   0.0071
  -6.250   0.0369   0.03964   0.03632  -0.1388   0.7262   0.0073
  -6.000   0.0475   0.03725   0.03381  -0.1382   0.7239   0.0074
  -5.750   0.0619   0.03519   0.03163  -0.1376   0.7215   0.0076
  -5.500   0.0777   0.03304   0.02934  -0.1370   0.7192   0.0078
  -5.250   0.0949   0.03088   0.02706  -0.1362   0.7172   0.0081
  -5.000   0.1130   0.02854   0.02457  -0.1353   0.7149   0.0085
  -4.750   0.1325   0.02600   0.02182  -0.1340   0.7127   0.0092
  -4.500   0.1571   0.02333   0.01885  -0.1321   0.7105   0.0100
  -4.250   0.1662   0.01633   0.01119  -0.1283   0.7085   0.0067
  -4.000   0.1888   0.01343   0.00780  -0.1269   0.7063   0.0067
  -3.750   0.2153   0.01261   0.00678  -0.1266   0.7044   0.0072
  -3.500   0.2399   0.01142   0.00544  -0.1262   0.7026   0.0074
  -3.250   0.2652   0.01076   0.00471  -0.1259   0.7005   0.0077
  -3.000   0.2908   0.01030   0.00421  -0.1257   0.6984   0.0079
  -2.750   0.3170   0.01001   0.00389  -0.1256   0.6964   0.0085
  -2.500   0.3436   0.00980   0.00364  -0.1257   0.6943   0.0093
  -2.250   0.3695   0.00947   0.00322  -0.1255   0.6920   0.0096
  -2.000   0.3957   0.00918   0.00290  -0.1254   0.6902   0.0099
  -1.750   0.4219   0.00888   0.00256  -0.1253   0.6884   0.0108
  -1.500   0.4483   0.00859   0.00233  -0.1252   0.6864   0.0286
  -1.250   0.4756   0.00849   0.00227  -0.1254   0.6845   0.0416
  -1.000   0.5031   0.00839   0.00220  -0.1257   0.6826   0.0574
  -0.750   0.5289   0.00806   0.00214  -0.1258   0.6807   0.1611
  -0.500   0.5434   0.00641   0.00216  -0.1244   0.6785   0.7666
  -0.250   0.5703   0.00647   0.00226  -0.1243   0.6765   0.8033
   0.000   0.5972   0.00652   0.00234  -0.1242   0.6748   0.8209
   0.250   0.6247   0.00658   0.00239  -0.1243   0.6729   0.8319
   0.500   0.6519   0.00666   0.00246  -0.1243   0.6710   0.8421
   0.750   0.6790   0.00672   0.00252  -0.1243   0.6692   0.8497
   1.000   0.7065   0.00678   0.00257  -0.1245   0.6674   0.8559
   1.250   0.7342   0.00685   0.00261  -0.1247   0.6655   0.8615
   1.500   0.7629   0.00694   0.00266  -0.1253   0.6633   0.8638
   1.750   0.7905   0.00697   0.00269  -0.1256   0.6617   0.8658
   2.000   0.8183   0.00700   0.00273  -0.1259   0.6600   0.8681
   2.250   0.8462   0.00704   0.00278  -0.1263   0.6581   0.8705
   2.500   0.8744   0.00708   0.00282  -0.1268   0.6563   0.8728
   2.750   0.9024   0.00712   0.00286  -0.1272   0.6545   0.8750
   3.000   0.9300   0.00716   0.00291  -0.1275   0.6526   0.8771
   3.250   0.9582   0.00724   0.00297  -0.1280   0.6507   0.8793
   3.500   0.9866   0.00733   0.00307  -0.1285   0.6487   0.8815
   3.750   1.0133   0.00738   0.00316  -0.1287   0.6471   0.8842
   4.000   1.0404   0.00743   0.00325  -0.1290   0.6451   0.8870
   4.250   1.0675   0.00747   0.00332  -0.1292   0.6429   0.8895
   4.500   1.0924   0.00746   0.00331  -0.1290   0.6382   0.8922
   4.750   1.1144   0.00745   0.00333  -0.1281   0.6302   0.8953
   5.000   1.1367   0.00747   0.00334  -0.1272   0.6222   0.8986
   5.250   1.1610   0.00752   0.00343  -0.1269   0.6176   0.9019
   5.500   1.1851   0.00756   0.00353  -0.1266   0.6135   0.9053
   5.750   1.2085   0.00763   0.00362  -0.1260   0.6095   0.9088
   6.000   1.2313   0.00770   0.00373  -0.1254   0.6047   0.9127
   6.250   1.2536   0.00777   0.00385  -0.1247   0.5990   0.9168
   6.500   1.2734   0.00787   0.00397  -0.1234   0.5934   0.9213
   6.750   1.2919   0.00791   0.00409  -0.1219   0.5874   0.9269
   7.000   1.3065   0.00803   0.00424  -0.1195   0.5801   0.9340
   7.250   1.3207   0.00814   0.00442  -0.1171   0.5711   0.9428
   7.500   1.3323   0.00831   0.00463  -0.1142   0.5612   0.9556
   7.750   1.3498   0.00856   0.00491  -0.1127   0.5460   0.9783
   8.000   1.3658   0.00898   0.00529  -0.1113   0.5254   1.0000
   8.250   1.3667   0.00976   0.00593  -0.1071   0.4917   1.0000
   8.500   1.3524   0.01119   0.00711  -0.1004   0.4419   1.0000
   8.750   1.3398   0.01279   0.00850  -0.0945   0.3994   1.0000
   9.000   1.3220   0.01484   0.01029  -0.0883   0.3515   1.0000
   9.250   1.3064   0.01699   0.01220  -0.0828   0.3038   1.0000
   9.500   1.3017   0.01873   0.01379  -0.0790   0.2712   1.0000
   9.750   1.2918   0.02085   0.01570  -0.0749   0.2306   1.0000
  10.000   1.2894   0.02265   0.01735  -0.0718   0.2007   1.0000
  10.250   1.2783   0.02507   0.01950  -0.0680   0.1572   1.0000
  10.500   1.2878   0.02624   0.02066  -0.0665   0.1461   1.0000
  10.750   1.2856   0.02823   0.02247  -0.0639   0.1169   1.0000
  11.000   1.2918   0.02971   0.02388  -0.0623   0.1012   1.0000
  11.250   1.2990   0.03115   0.02527  -0.0608   0.0875   1.0000
  11.500   1.3071   0.03256   0.02664  -0.0595   0.0759   1.0000
  11.750   1.3146   0.03403   0.02808  -0.0581   0.0650   1.0000
  12.000   1.3192   0.03575   0.02970  -0.0566   0.0498   1.0000
  12.250   1.3278   0.03721   0.03115  -0.0555   0.0423   1.0000
  12.500   1.3362   0.03871   0.03263  -0.0544   0.0357   1.0000
  12.750   1.3431   0.04035   0.03423  -0.0533   0.0274   1.0000
  13.000   1.3530   0.04178   0.03569  -0.0525   0.0237   1.0000
  13.250   1.3607   0.04340   0.03729  -0.0515   0.0181   1.0000
  13.500   1.3679   0.04511   0.03899  -0.0506   0.0139   1.0000
  13.750   1.3749   0.04686   0.04074  -0.0497   0.0097   1.0000
  14.000   1.3689   0.04985   0.04366  -0.0479   0.0013   1.0000
  14.250   1.3768   0.05161   0.04548  -0.0471   0.0009   1.0000
  14.500   1.3922   0.05267   0.04661  -0.0471   0.0019   1.0000
  14.750   1.3918   0.05531   0.04932  -0.0459   0.0006   1.0000
  15.000   1.4003   0.05709   0.05118  -0.0454   0.0006   1.0000
  15.250   1.4020   0.05965   0.05386  -0.0445   0.0005   1.0000
  15.500   1.4028   0.06233   0.05665  -0.0437   0.0004   1.0000
  15.750   1.4110   0.06425   0.05863  -0.0435   0.0004   1.0000
  16.000   1.4126   0.06695   0.06146  -0.0429   0.0004   1.0000
  16.250   1.4155   0.06958   0.06419  -0.0426   0.0004   1.0000
  16.500   1.4168   0.07243   0.06715  -0.0423   0.0004   1.0000
  16.750   1.4191   0.07521   0.07002  -0.0422   0.0004   1.0000
  17.000   1.4203   0.07818   0.07309  -0.0421   0.0004   1.0000
  17.250   1.4186   0.08159   0.07662  -0.0421   0.0004   1.0000
  17.500   1.4194   0.08474   0.07987  -0.0423   0.0004   1.0000
  17.750   1.4169   0.08841   0.08365  -0.0425   0.0004   1.0000
  18.000   1.4099   0.09279   0.08818  -0.0430   0.0003   1.0000
  18.250   1.4071   0.09663   0.09213  -0.0436   0.0003   1.0000
  18.500   1.3982   0.10149   0.09713  -0.0444   0.0003   1.0000
  18.750   1.3951   0.10555   0.10131  -0.0454   0.0003   1.0000
  19.000   1.3897   0.11003   0.10591  -0.0465   0.0003   1.0000
  19.250   1.3817   0.11505   0.11106  -0.0480   0.0003   1.0000
<< Back to NREL's S832 Airfoil (s832-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S832 Airfoil (s832-nr)