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NREL's S832 Airfoil (s832-nr) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NREL's S832 Airfoil (s832-nr)
Reynolds number: 100,000
Max Cl/Cd: 25.18 at α=11.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s832-nr-100000-n5.txt
Download as CSV file: xf-s832-nr-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.0315   0.11587   0.11036  -0.1212   0.8874   0.0334
 -11.250  -0.0307   0.11370   0.10820  -0.1236   0.8821   0.0338
 -11.000  -0.0273   0.11115   0.10564  -0.1260   0.8780   0.0340
 -10.750  -0.0225   0.10850   0.10299  -0.1273   0.8726   0.0340
 -10.500  -0.0203   0.10580   0.10031  -0.1294   0.8675   0.0341
 -10.000  -0.0101   0.09902   0.09353  -0.1318   0.8592   0.0345
  -9.750   0.0070   0.09484   0.08931  -0.1296   0.8562   0.0359
  -9.500   0.0156   0.09209   0.08654  -0.1297   0.8526   0.0376
  -9.250   0.0215   0.08943   0.08386  -0.1307   0.8492   0.0395
  -9.000   0.0221   0.08704   0.08150  -0.1320   0.8439   0.0424
  -8.750   0.0249   0.08430   0.07878  -0.1329   0.8393   0.0421
  -8.500   0.0235   0.08170   0.07618  -0.1355   0.8352   0.0439
  -8.250   0.0107   0.07944   0.07398  -0.1394   0.8284   0.0449
  -8.000   0.0058   0.07700   0.07151  -0.1399   0.8237   0.0449
  -7.750  -0.0007   0.07496   0.06938  -0.1402   0.8200   0.0451
  -7.500  -0.0140   0.07407   0.06839  -0.1393   0.8132   0.0454
  -7.250  -0.0166   0.07221   0.06639  -0.1385   0.8089   0.0456
  -7.000  -0.0066   0.06632   0.06066  -0.1384   0.8070   0.0470
  -6.750  -0.0020   0.06377   0.05809  -0.1374   0.8036   0.0477
  -6.500  -0.0030   0.06181   0.05612  -0.1355   0.7985   0.0485
  -6.250   0.0011   0.05946   0.05368  -0.1344   0.7948   0.0494
  -6.000   0.0090   0.05689   0.05098  -0.1338   0.7922   0.0505
  -5.750   0.0091   0.05519   0.04916  -0.1314   0.7872   0.0510
  -5.500   0.0159   0.05237   0.04583  -0.1283   0.7823   0.0336
  -5.000   0.0394   0.04558   0.03854  -0.1255   0.7776   0.0246
  -4.750   0.0367   0.04459   0.03747  -0.1214   0.7714   0.0241
  -4.500   0.0462   0.04262   0.03528  -0.1191   0.7675   0.0235
  -4.250   0.0638   0.04028   0.03263  -0.1178   0.7651   0.0228
  -4.000   0.0856   0.03794   0.02992  -0.1170   0.7635   0.0222
  -3.750   0.0836   0.03740   0.02922  -0.1123   0.7573   0.0219
  -3.500   0.0975   0.03595   0.02745  -0.1100   0.7535   0.0215
  -3.250   0.1215   0.03409   0.02521  -0.1091   0.7514   0.0214
  -3.000   0.1497   0.03230   0.02301  -0.1088   0.7499   0.0217
  -2.750   0.1796   0.03079   0.02115  -0.1088   0.7488   0.0232
  -2.500   0.1662   0.03163   0.02196  -0.1025   0.7405   0.0235
  -2.250   0.1899   0.03069   0.02076  -0.1015   0.7382   0.0262
  -2.000   0.2170   0.02975   0.01974  -0.1015   0.7366   0.0285
  -1.750   0.2460   0.02878   0.01865  -0.1014   0.7353   0.0315
  -1.500   0.2288   0.03003   0.01985  -0.0946   0.7268   0.0335
  -1.250   0.2479   0.02960   0.01947  -0.0934   0.7242   0.0393
  -1.000   0.2720   0.02900   0.01881  -0.0927   0.7226   0.0497
  -0.750   0.2987   0.02846   0.01819  -0.0925   0.7213   0.0641
  -0.500   0.3276   0.02794   0.01761  -0.0927   0.7202   0.0908
   0.250   0.3155   0.02808   0.02031  -0.0749   0.7068   0.8917
   0.500   0.3425   0.02916   0.02133  -0.0747   0.7026   0.9616
   1.000   0.5207   0.02892   0.02043  -0.0980   0.7066   1.0000
   1.500   0.4714   0.03108   0.02257  -0.0823   0.6930   1.0000
   2.500   0.5128   0.03347   0.02463  -0.0741   0.6782   1.0000
   2.750   0.5025   0.03544   0.02657  -0.0702   0.6698   1.0000
   3.000   0.5252   0.03586   0.02691  -0.0701   0.6671   1.0000
   3.250   0.5515   0.03614   0.02713  -0.0703   0.6653   1.0000
   3.500   0.5798   0.03634   0.02727  -0.0708   0.6640   1.0000
   4.000   0.5973   0.03873   0.02961  -0.0677   0.6527   1.0000
   4.250   0.6249   0.03897   0.02983  -0.0681   0.6510   1.0000
   4.500   0.6548   0.03907   0.02991  -0.0688   0.6496   1.0000
   5.000   0.6748   0.04140   0.03227  -0.0660   0.6378   1.0000
   5.250   0.7042   0.04150   0.03238  -0.0666   0.6362   1.0000
   5.750   0.7283   0.04360   0.03453  -0.0643   0.6243   1.0000
   6.000   0.7577   0.04365   0.03461  -0.0648   0.6224   1.0000
   6.500   0.7851   0.04550   0.03658  -0.0628   0.6102   1.0000
   6.750   0.8158   0.04538   0.03652  -0.0633   0.6083   1.0000
   7.250   0.8464   0.04692   0.03822  -0.0616   0.5956   1.0000
   7.500   0.8793   0.04648   0.03788  -0.0622   0.5936   1.0000
   8.000   0.9145   0.04742   0.03902  -0.0607   0.5801   1.0000
   8.500   0.9544   0.04774   0.03956  -0.0593   0.5662   1.0000
   9.000   0.9987   0.04737   0.03946  -0.0580   0.5516   1.0000
   9.250   1.0062   0.04837   0.04057  -0.0564   0.5395   1.0000
   9.500   1.0176   0.04907   0.04140  -0.0551   0.5280   1.0000
   9.750   1.0508   0.04772   0.04021  -0.0549   0.5233   1.0000
  10.250   1.0711   0.04943   0.04222  -0.0523   0.4968   1.0000
  10.750   1.1036   0.05004   0.04312  -0.0503   0.4669   1.0000
  11.000   1.1159   0.05083   0.04403  -0.0491   0.4461   1.0000
  11.250   1.1458   0.04961   0.04290  -0.0485   0.4231   1.0000
  11.500   1.1781   0.04805   0.04125  -0.0478   0.3865   1.0000
  11.750   1.1993   0.04763   0.04057  -0.0465   0.3410   1.0000
  12.000   1.2051   0.04899   0.04168  -0.0447   0.2989   1.0000
  12.250   1.2065   0.05098   0.04348  -0.0430   0.2636   1.0000
  12.500   1.2076   0.05316   0.04551  -0.0416   0.2324   1.0000
  12.750   1.2086   0.05545   0.04770  -0.0403   0.2047   1.0000
  13.000   1.2103   0.05776   0.04992  -0.0392   0.1813   1.0000
  13.250   1.2130   0.06005   0.05216  -0.0382   0.1601   1.0000
  13.500   1.2150   0.06245   0.05450  -0.0373   0.1416   1.0000
  13.750   1.2185   0.06478   0.05684  -0.0366   0.1242   1.0000
  14.000   1.2215   0.06723   0.05928  -0.0359   0.1087   1.0000
  14.250   1.2243   0.06973   0.06180  -0.0354   0.0951   1.0000
  14.500   1.2269   0.07232   0.06442  -0.0349   0.0831   1.0000
  14.750   1.2290   0.07501   0.06715  -0.0344   0.0727   1.0000
  15.000   1.2302   0.07789   0.07005  -0.0341   0.0632   1.0000
  15.250   1.2297   0.08101   0.07321  -0.0339   0.0557   1.0000
  15.500   1.2321   0.08385   0.07619  -0.0337   0.0482   1.0000
  15.750   1.2315   0.08710   0.07949  -0.0336   0.0427   1.0000
  16.000   1.2317   0.09032   0.08284  -0.0337   0.0378   1.0000
  16.250   1.2299   0.09384   0.08643  -0.0338   0.0340   1.0000
  16.500   1.2299   0.09718   0.08994  -0.0340   0.0302   1.0000
  16.750   1.2255   0.10117   0.09397  -0.0346   0.0274   1.0000
  17.000   1.2265   0.10447   0.09749  -0.0349   0.0247   1.0000
  17.250   1.2243   0.10830   0.10146  -0.0357   0.0223   1.0000
  17.500   1.2201   0.11246   0.10569  -0.0368   0.0207   1.0000
  17.750   1.2187   0.11631   0.10976  -0.0377   0.0186   1.0000
  18.000   1.2155   0.12056   0.11420  -0.0390   0.0168   1.0000
  18.250   1.2117   0.12490   0.11865  -0.0406   0.0157   1.0000
  18.500   1.2049   0.12987   0.12373  -0.0427   0.0144   1.0000
  18.750   1.2014   0.13441   0.12856  -0.0444   0.0134   1.0000
  19.000   1.1971   0.13915   0.13351  -0.0465   0.0127   1.0000
  19.250   1.1915   0.14430   0.13884  -0.0490   0.0120   1.0000
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