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NREL's S823 Airfoil (s823-nr) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NREL's S823 Airfoil (s823-nr)
Reynolds number: 100,000
Max Cl/Cd: 42.33 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s823-nr-100000.txt
Download as CSV file: xf-s823-nr-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S823 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1850   0.13559   0.12910  -0.0172   1.0000   0.2382
  -8.000  -0.1957   0.13541   0.12900  -0.0145   1.0000   0.2409
  -7.750  -0.2786   0.13836   0.13203  -0.0130   1.0000   0.2455
  -7.500  -0.2390   0.13380   0.12750  -0.0145   0.9974   0.2462
  -7.250  -0.1925   0.12958   0.12329  -0.0182   0.9933   0.2476
  -7.000  -0.1561   0.12634   0.12006  -0.0218   0.9879   0.2501
  -6.750  -0.1266   0.12340   0.11713  -0.0262   0.9828   0.2543
  -6.500  -0.1595   0.12144   0.11513  -0.0329   0.9739   0.2617
  -6.250  -0.1123   0.11694   0.11065  -0.0362   0.9698   0.2626
  -6.000  -0.0735   0.11346   0.10719  -0.0392   0.9643   0.2643
  -5.750  -0.0420   0.11046   0.10421  -0.0425   0.9578   0.2668
  -4.750  -0.0443   0.08954   0.08310  -0.0629   0.9270   0.2447
  -4.500  -0.0015   0.08639   0.07995  -0.0668   0.9242   0.2429
  -4.250   0.0063   0.08300   0.07657  -0.0683   0.9134   0.2415
  -4.000   0.0200   0.07754   0.07107  -0.0740   0.9089   0.2401
  -3.750   0.1027   0.08130   0.07500  -0.0753   0.9076   0.2676
  -3.500   0.1172   0.08034   0.07410  -0.0756   0.8965   0.2813
  -3.250  -0.2592   0.03696   0.02879  -0.0912   0.8491   0.2551
  -3.000  -0.2185   0.03504   0.02660  -0.0957   0.8445   0.2629
  -2.750  -0.1680   0.03495   0.02674  -0.0986   0.8421   0.2684
  -2.500  -0.1585   0.03464   0.02631  -0.0970   0.8299   0.2742
  -2.250  -0.1108   0.03395   0.02569  -0.1004   0.8270   0.2815
  -2.000  -0.0954   0.03418   0.02600  -0.0987   0.8167   0.2864
  -1.750  -0.0513   0.03310   0.02479  -0.1023   0.8122   0.2955
  -1.500  -0.0011   0.03286   0.02473  -0.1053   0.8095   0.3024
  -1.250   0.0110   0.03243   0.02406  -0.1045   0.7983   0.3101
  -1.000   0.0543   0.03237   0.02427  -0.1060   0.7945   0.3159
  -0.750   0.1052   0.03139   0.02317  -0.1103   0.7917   0.3271
  -0.500   0.1102   0.03208   0.02403  -0.1066   0.7797   0.3306
  -0.250   0.1588   0.03130   0.02313  -0.1103   0.7763   0.3421
   0.000   0.1684   0.03188   0.02390  -0.1073   0.7658   0.3462
   0.250   0.2091   0.03155   0.02363  -0.1091   0.7611   0.3551
   0.500   0.2558   0.03094   0.02308  -0.1117   0.7580   0.3638
   0.750   0.2603   0.03162   0.02383  -0.1084   0.7463   0.3693
   1.000   0.3058   0.03095   0.02317  -0.1111   0.7425   0.3792
   1.250   0.3145   0.03161   0.02393  -0.1083   0.7322   0.3847
   1.500   0.3561   0.03100   0.02329  -0.1105   0.7274   0.3947
   1.750   0.4015   0.03056   0.02294  -0.1125   0.7240   0.4040
   2.000   0.4057   0.03121   0.02360  -0.1098   0.7125   0.4108
   2.250   0.4481   0.03084   0.02335  -0.1111   0.7085   0.4195
   2.500   0.4575   0.03141   0.02392  -0.1092   0.6982   0.4271
   2.750   0.4953   0.03115   0.02380  -0.1099   0.6933   0.4353
   3.000   0.5417   0.03055   0.02322  -0.1123   0.6895   0.4464
   3.250   0.5428   0.03154   0.02434  -0.1086   0.6781   0.4522
   3.500   0.5910   0.03083   0.02366  -0.1110   0.6742   0.4636
   3.750   0.5928   0.03186   0.02482  -0.1075   0.6632   0.4699
   4.000   0.6389   0.03118   0.02419  -0.1095   0.6585   0.4814
   4.250   0.6488   0.03192   0.02502  -0.1071   0.6484   0.4895
   4.500   0.6911   0.03131   0.02450  -0.1083   0.6426   0.5001
   4.750   0.7124   0.03162   0.02483  -0.1075   0.6334   0.5110
   5.000   0.7479   0.03120   0.02455  -0.1075   0.6263   0.5205
   5.250   0.7724   0.03129   0.02471  -0.1068   0.6173   0.5308
   5.500   0.8118   0.03075   0.02420  -0.1078   0.6093   0.5440
   5.750   0.8304   0.03094   0.02456  -0.1057   0.5996   0.5520
   6.000   0.8739   0.03015   0.02379  -0.1070   0.5914   0.5651
   6.250   0.8919   0.03037   0.02412  -0.1052   0.5802   0.5760
   6.500   0.9426   0.02927   0.02301  -0.1070   0.5723   0.5894
   6.750   0.9555   0.02951   0.02340  -0.1044   0.5598   0.5994
   7.000   0.9809   0.02937   0.02332  -0.1035   0.5481   0.6125
   7.250   1.0186   0.02866   0.02263  -0.1036   0.5374   0.6254
   7.500   1.0412   0.02840   0.02247  -0.1018   0.5245   0.6369
   7.750   1.0604   0.02829   0.02246  -0.0998   0.5107   0.6494
   8.000   1.0831   0.02805   0.02227  -0.0983   0.4965   0.6632
   8.250   1.1036   0.02779   0.02209  -0.0962   0.4818   0.6761
   8.500   1.1219   0.02755   0.02191  -0.0937   0.4662   0.6890
   8.750   1.1373   0.02740   0.02182  -0.0910   0.4496   0.7024
   9.000   1.1494   0.02733   0.02180  -0.0879   0.4318   0.7166
   9.250   1.1574   0.02734   0.02185  -0.0842   0.4133   0.7312
   9.500   1.1620   0.02745   0.02198  -0.0801   0.3941   0.7462
   9.750   1.1676   0.02769   0.02216  -0.0763   0.3736   0.7622
  10.000   1.1652   0.02834   0.02286  -0.0718   0.3518   0.7783
  10.250   1.1635   0.02906   0.02356  -0.0676   0.3295   0.7958
  10.500   1.1609   0.02993   0.02433  -0.0634   0.3078   0.8148
  10.750   1.1547   0.03106   0.02547  -0.0593   0.2860   0.8370
  11.000   1.1478   0.03223   0.02660  -0.0552   0.2663   0.8651
  11.250   1.1377   0.03324   0.02762  -0.0505   0.2492   0.9131
  11.500   1.1404   0.03491   0.02907  -0.0496   0.2287   1.0000
  11.750   1.1463   0.03730   0.03132  -0.0499   0.2075   1.0000
  12.000   1.1513   0.03964   0.03350  -0.0497   0.1892   1.0000
  12.250   1.1556   0.04198   0.03568  -0.0492   0.1733   1.0000
  12.500   1.1600   0.04432   0.03789  -0.0486   0.1592   1.0000
  12.750   1.1650   0.04664   0.04006  -0.0480   0.1466   1.0000
  13.000   1.1717   0.04886   0.04210  -0.0475   0.1352   1.0000
  13.250   1.1737   0.05142   0.04470  -0.0470   0.1252   1.0000
  13.500   1.1793   0.05386   0.04711  -0.0465   0.1158   1.0000
  13.750   1.1899   0.05593   0.04894  -0.0460   0.1069   1.0000
  14.000   1.1897   0.05884   0.05203  -0.0457   0.1000   1.0000
  14.250   1.2018   0.06091   0.05390  -0.0453   0.0929   1.0000
  14.500   1.2017   0.06397   0.05715  -0.0452   0.0873   1.0000
  14.750   1.2187   0.06573   0.05864  -0.0447   0.0810   1.0000
  15.000   1.2156   0.06921   0.06241  -0.0448   0.0771   1.0000
  15.250   1.2204   0.07193   0.06515  -0.0448   0.0729   1.0000
  15.500   1.2344   0.07419   0.06731  -0.0444   0.0686   1.0000
  15.750   1.2303   0.07803   0.07141  -0.0449   0.0659   1.0000
  16.000   1.2310   0.08142   0.07493  -0.0453   0.0631   1.0000
  16.250   1.2509   0.08296   0.07623  -0.0448   0.0596   1.0000
  16.500   1.2439   0.08748   0.08101  -0.0457   0.0580   1.0000
  16.750   1.2314   0.09257   0.08640  -0.0472   0.0566   1.0000
  17.000   1.2208   0.09765   0.09172  -0.0489   0.0552   1.0000
  17.250   1.2120   0.10265   0.09692  -0.0507   0.0540   1.0000
  17.500   1.2012   0.10808   0.10255  -0.0530   0.0530   1.0000
  17.750   1.1905   0.11358   0.10821  -0.0555   0.0521   1.0000
  18.000   1.1833   0.11867   0.11341  -0.0579   0.0513   1.0000
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