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NREL's S832 Airfoil (s832-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NREL's S832 Airfoil (s832-nr)
Reynolds number: 1,000,000
Max Cl/Cd: 151.19 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s832-nr-1000000-n5.txt
Download as CSV file: xf-s832-nr-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.0109   0.08414   0.08110  -0.1258   0.7313   0.0047
  -9.500   0.0151   0.08106   0.07804  -0.1271   0.7290   0.0047
  -9.250   0.0190   0.07806   0.07504  -0.1284   0.7264   0.0047
  -9.000   0.0214   0.07482   0.07181  -0.1298   0.7237   0.0047
  -8.750   0.0240   0.07182   0.06880  -0.1312   0.7211   0.0047
  -8.500   0.0256   0.06867   0.06566  -0.1327   0.7185   0.0047
  -8.250   0.0236   0.06499   0.06202  -0.1349   0.7160   0.0047
  -6.250   0.0176   0.03714   0.03359  -0.1361   0.6957   0.0027
  -6.000   0.0275   0.03347   0.02971  -0.1347   0.6935   0.0027
  -5.500   0.0226   0.01400   0.00845  -0.1241   0.6898   0.0031
  -5.250   0.0481   0.01334   0.00768  -0.1241   0.6879   0.0033
  -5.000   0.0737   0.01265   0.00686  -0.1239   0.6858   0.0034
  -4.750   0.0996   0.01213   0.00625  -0.1238   0.6836   0.0035
  -4.500   0.1255   0.01167   0.00569  -0.1238   0.6813   0.0037
  -4.250   0.1511   0.01120   0.00512  -0.1236   0.6792   0.0039
  -4.000   0.1766   0.01079   0.00461  -0.1234   0.6772   0.0040
  -3.750   0.2028   0.01042   0.00419  -0.1233   0.6755   0.0042
  -3.500   0.2289   0.01009   0.00381  -0.1233   0.6736   0.0043
  -3.250   0.2554   0.00987   0.00355  -0.1233   0.6717   0.0046
  -3.000   0.2817   0.00962   0.00326  -0.1232   0.6696   0.0048
  -2.750   0.3073   0.00930   0.00289  -0.1231   0.6676   0.0052
  -2.500   0.3337   0.00911   0.00267  -0.1231   0.6655   0.0055
  -2.250   0.3601   0.00895   0.00246  -0.1230   0.6635   0.0058
  -2.000   0.3872   0.00880   0.00229  -0.1232   0.6617   0.0063
  -1.750   0.4145   0.00867   0.00214  -0.1233   0.6599   0.0070
  -1.500   0.4415   0.00852   0.00201  -0.1234   0.6580   0.0147
  -1.250   0.4687   0.00841   0.00195  -0.1236   0.6560   0.0242
  -1.000   0.4959   0.00834   0.00190  -0.1238   0.6541   0.0345
  -0.750   0.5229   0.00825   0.00186  -0.1240   0.6523   0.0515
  -0.500   0.5498   0.00817   0.00181  -0.1241   0.6504   0.0758
  -0.250   0.5724   0.00740   0.00178  -0.1240   0.6486   0.3649
   0.000   0.5920   0.00632   0.00182  -0.1232   0.6467   0.7574
   0.250   0.6196   0.00633   0.00186  -0.1234   0.6448   0.7826
   0.500   0.6472   0.00637   0.00190  -0.1235   0.6429   0.7994
   0.750   0.6745   0.00641   0.00195  -0.1237   0.6410   0.8113
   1.000   0.7019   0.00646   0.00199  -0.1239   0.6392   0.8188
   1.250   0.7294   0.00652   0.00203  -0.1241   0.6374   0.8260
   1.500   0.7571   0.00659   0.00206  -0.1244   0.6356   0.8289
   1.750   0.7849   0.00662   0.00210  -0.1247   0.6339   0.8309
   2.000   0.8127   0.00665   0.00214  -0.1251   0.6320   0.8330
   2.250   0.8404   0.00670   0.00219  -0.1254   0.6301   0.8350
   2.500   0.8680   0.00675   0.00224  -0.1257   0.6283   0.8372
   2.750   0.8955   0.00680   0.00231  -0.1260   0.6264   0.8393
   3.000   0.9228   0.00686   0.00237  -0.1263   0.6246   0.8416
   3.250   0.9499   0.00694   0.00243  -0.1265   0.6227   0.8438
   3.500   0.9767   0.00701   0.00250  -0.1267   0.6208   0.8461
   3.750   1.0038   0.00706   0.00260  -0.1269   0.6191   0.8483
   4.000   1.0308   0.00711   0.00269  -0.1271   0.6172   0.8505
   4.250   1.0574   0.00717   0.00278  -0.1273   0.6149   0.8529
   4.500   1.0819   0.00725   0.00285  -0.1270   0.6096   0.8555
   4.750   1.1038   0.00734   0.00294  -0.1261   0.5982   0.8584
   5.000   1.1232   0.00747   0.00305  -0.1248   0.5843   0.8614
   5.250   1.1437   0.00760   0.00318  -0.1236   0.5748   0.8644
   5.500   1.1638   0.00771   0.00331  -0.1224   0.5675   0.8677
   5.750   1.1838   0.00783   0.00345  -0.1212   0.5613   0.8711
   6.000   1.2007   0.00802   0.00363  -0.1194   0.5518   0.8746
   6.250   1.2161   0.00824   0.00386  -0.1173   0.5391   0.8786
   6.500   1.2284   0.00855   0.00415  -0.1147   0.5234   0.8836
   7.000   1.2379   0.00966   0.00511  -0.1068   0.4697   0.8962
   7.250   1.2271   0.01079   0.00606  -0.1003   0.4259   0.9060
   7.750   1.2094   0.01325   0.00828  -0.0889   0.3506   0.9408
   8.250   1.2129   0.01607   0.01083  -0.0831   0.2803   1.0000
   8.500   1.2155   0.01737   0.01203  -0.0802   0.2540   1.0000
   8.750   1.2144   0.01893   0.01344  -0.0770   0.2230   1.0000
   9.000   1.2155   0.02044   0.01482  -0.0742   0.1954   1.0000
   9.250   1.2211   0.02174   0.01603  -0.0720   0.1747   1.0000
   9.500   1.2264   0.02310   0.01731  -0.0699   0.1556   1.0000
   9.750   1.2334   0.02439   0.01854  -0.0681   0.1385   1.0000
  10.000   1.2384   0.02585   0.01990  -0.0661   0.1187   1.0000
  10.250   1.2377   0.02773   0.02161  -0.0636   0.0905   1.0000
  10.500   1.2514   0.02867   0.02259  -0.0627   0.0864   1.0000
  10.750   1.2518   0.03057   0.02432  -0.0605   0.0606   1.0000
  11.000   1.2559   0.03226   0.02592  -0.0588   0.0442   1.0000
  11.250   1.2659   0.03356   0.02718  -0.0577   0.0366   1.0000
  11.500   1.2773   0.03477   0.02841  -0.0567   0.0321   1.0000
  11.750   1.2873   0.03609   0.02971  -0.0557   0.0264   1.0000
  12.000   1.2937   0.03773   0.03132  -0.0544   0.0174   1.0000
  12.250   1.3041   0.03908   0.03268  -0.0535   0.0145   1.0000
  12.500   1.3163   0.04031   0.03394  -0.0528   0.0128   1.0000
  12.750   1.3233   0.04197   0.03559  -0.0517   0.0081   1.0000
  13.000   1.3347   0.04330   0.03695  -0.0511   0.0072   1.0000
  13.250   1.3429   0.04493   0.03858  -0.0502   0.0045   1.0000
  13.500   1.3517   0.04653   0.04022  -0.0494   0.0030   1.0000
  13.750   1.3597   0.04823   0.04195  -0.0486   0.0012   1.0000
  14.000   1.3650   0.05020   0.04397  -0.0477   0.0003   1.0000
  14.250   1.3752   0.05174   0.04557  -0.0471   0.0002   1.0000
  14.750   1.3919   0.05526   0.04921  -0.0460   0.0001   1.0000
  15.000   1.4017   0.05692   0.05093  -0.0456   0.0001   1.0000
  15.250   1.4066   0.05911   0.05321  -0.0450   0.0001   1.0000
  15.500   1.4138   0.06107   0.05525  -0.0445   0.0001   1.0000
  15.750   1.4216   0.06300   0.05724  -0.0442   0.0001   1.0000
  16.000   1.4274   0.06518   0.05952  -0.0438   0.0001   1.0000
  16.250   1.4336   0.06735   0.06178  -0.0435   0.0001   1.0000
  16.500   1.4374   0.06983   0.06436  -0.0433   0.0000   1.0000
  16.750   1.4434   0.07210   0.06669  -0.0431   0.0000   1.0000
  17.000   1.4479   0.07458   0.06926  -0.0430   0.0000   1.0000
  17.250   1.4493   0.07744   0.07223  -0.0429   0.0000   1.0000
  17.500   1.4542   0.07994   0.07481  -0.0430   0.0000   1.0000
  17.750   1.4564   0.08283   0.07779  -0.0431   0.0000   1.0000
  18.000   1.4550   0.08625   0.08134  -0.0433   0.0000   1.0000
  18.250   1.4557   0.08944   0.08462  -0.0436   0.0000   1.0000
  18.500   1.4526   0.09319   0.08850  -0.0440   0.0000   1.0000
  18.750   1.4538   0.09639   0.09180  -0.0446   0.0000   1.0000
  19.000   1.4514   0.10017   0.09570  -0.0453   0.0000   1.0000
  19.250   1.4482   0.10414   0.09979  -0.0462   0.0000   1.0000
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