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NREL's S823 Airfoil (s823-nr) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NREL's S823 Airfoil (s823-nr)
Reynolds number: 200,000
Max Cl/Cd: 62.49 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s823-nr-200000.txt
Download as CSV file: xf-s823-nr-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.8014   0.04573   0.03955  -0.0663   0.9923   0.1642
  -9.250  -0.8091   0.04034   0.03384  -0.0745   0.9810   0.1651
  -9.000  -0.8002   0.03716   0.03042  -0.0796   0.9696   0.1661
  -8.750  -0.7813   0.03490   0.02796  -0.0832   0.9601   0.1672
  -8.500  -0.7501   0.03299   0.02584  -0.0877   0.9548   0.1683
  -8.250  -0.7285   0.03160   0.02427  -0.0894   0.9454   0.1692
  -8.000  -0.6952   0.02982   0.02246  -0.0924   0.9415   0.1710
  -7.750  -0.6640   0.02888   0.02155  -0.0942   0.9357   0.1726
  -7.500  -0.6322   0.02809   0.02076  -0.0960   0.9293   0.1742
  -7.250  -0.5928   0.02720   0.01987  -0.0992   0.9261   0.1763
  -7.000  -0.5575   0.02632   0.01893  -0.1017   0.9216   0.1784
  -6.750  -0.5288   0.02546   0.01798  -0.1031   0.9140   0.1807
  -6.500  -0.4884   0.02448   0.01683  -0.1067   0.9109   0.1832
  -6.250  -0.4451   0.02335   0.01574  -0.1103   0.9089   0.1863
  -6.000  -0.4164   0.02281   0.01526  -0.1110   0.9007   0.1888
  -5.750  -0.3767   0.02218   0.01465  -0.1138   0.8961   0.1923
  -5.500  -0.3331   0.02147   0.01384  -0.1175   0.8927   0.1966
  -5.250  -0.3055   0.02087   0.01318  -0.1181   0.8835   0.2003
  -5.000  -0.2666   0.02031   0.01273  -0.1205   0.8781   0.2046
  -4.750  -0.2333   0.01994   0.01235  -0.1219   0.8706   0.2092
  -4.500  -0.2006   0.01952   0.01176  -0.1234   0.8624   0.2141
  -4.250  -0.1682   0.01901   0.01138  -0.1244   0.8549   0.2187
  -4.000  -0.1383   0.01875   0.01112  -0.1251   0.8457   0.2235
  -3.750  -0.1072   0.01847   0.01071  -0.1260   0.8376   0.2290
  -3.500  -0.0786   0.01811   0.01044  -0.1263   0.8287   0.2338
  -3.250  -0.0492   0.01795   0.01028  -0.1267   0.8202   0.2389
  -3.000  -0.0195   0.01775   0.00995  -0.1272   0.8113   0.2448
  -2.750   0.0082   0.01750   0.00980  -0.1273   0.8029   0.2497
  -2.500   0.0375   0.01737   0.00968  -0.1276   0.7944   0.2552
  -2.250   0.0661   0.01726   0.00943  -0.1279   0.7859   0.2612
  -2.000   0.0945   0.01705   0.00933  -0.1280   0.7775   0.2663
  -1.750   0.1227   0.01700   0.00928  -0.1281   0.7694   0.2724
  -1.500   0.1516   0.01686   0.00908  -0.1283   0.7611   0.2788
  -1.250   0.1799   0.01680   0.00911  -0.1283   0.7533   0.2844
  -1.000   0.2083   0.01676   0.00902  -0.1284   0.7450   0.2913
  -0.750   0.2376   0.01666   0.00894  -0.1286   0.7378   0.2973
  -0.500   0.2645   0.01664   0.00898  -0.1284   0.7292   0.3035
  -0.250   0.2960   0.01658   0.00882  -0.1290   0.7227   0.3108
   0.000   0.3212   0.01657   0.00895  -0.1284   0.7140   0.3167
   0.250   0.3530   0.01659   0.00887  -0.1290   0.7075   0.3250
   0.500   0.3781   0.01657   0.00899  -0.1284   0.6991   0.3312
   0.750   0.4083   0.01658   0.00899  -0.1287   0.6923   0.3389
   1.000   0.4356   0.01657   0.00902  -0.1285   0.6848   0.3458
   1.250   0.4640   0.01659   0.00910  -0.1284   0.6775   0.3528
   1.500   0.4941   0.01660   0.00905  -0.1287   0.6711   0.3606
   1.750   0.5200   0.01661   0.00921  -0.1282   0.6631   0.3667
   2.000   0.5520   0.01666   0.00914  -0.1287   0.6571   0.3754
   2.250   0.5767   0.01668   0.00935  -0.1280   0.6494   0.3817
   2.500   0.6065   0.01673   0.00938  -0.1281   0.6427   0.3902
   2.750   0.6342   0.01677   0.00950  -0.1279   0.6360   0.3971
   3.000   0.6614   0.01683   0.00962  -0.1276   0.6285   0.4050
   3.250   0.6929   0.01687   0.00964  -0.1280   0.6224   0.4131
   3.500   0.7168   0.01696   0.00986  -0.1270   0.6139   0.4211
   3.750   0.7474   0.01697   0.00985  -0.1272   0.6070   0.4294
   4.000   0.7716   0.01705   0.01005  -0.1263   0.5982   0.4375
   4.250   0.8014   0.01706   0.01006  -0.1263   0.5907   0.4462
   4.500   0.8258   0.01715   0.01026  -0.1254   0.5819   0.4547
   4.750   0.8549   0.01717   0.01027  -0.1253   0.5739   0.4634
   5.000   0.8788   0.01725   0.01047  -0.1242   0.5646   0.4723
   5.250   0.9079   0.01728   0.01048  -0.1241   0.5562   0.4812
   5.500   0.9305   0.01736   0.01068  -0.1228   0.5461   0.4904
   5.750   0.9577   0.01741   0.01075  -0.1223   0.5373   0.4992
   6.000   0.9810   0.01748   0.01088  -0.1211   0.5267   0.5094
   6.250   1.0044   0.01754   0.01106  -0.1200   0.5165   0.5177
   6.500   1.0306   0.01761   0.01108  -0.1193   0.5060   0.5283
   6.750   1.0499   0.01767   0.01132  -0.1174   0.4939   0.5370
   7.000   1.0717   0.01777   0.01147  -0.1159   0.4818   0.5471
   7.250   1.0928   0.01788   0.01162  -0.1143   0.4692   0.5571
   7.500   1.1127   0.01800   0.01176  -0.1126   0.4557   0.5668
   7.750   1.1302   0.01816   0.01197  -0.1104   0.4406   0.5780
   8.000   1.1454   0.01833   0.01224  -0.1079   0.4246   0.5870
   8.250   1.1595   0.01857   0.01250  -0.1052   0.4074   0.5977
   8.500   1.1690   0.01884   0.01279  -0.1018   0.3891   0.6079
   8.750   1.1775   0.01921   0.01319  -0.0983   0.3685   0.6179
   9.000   1.1851   0.01976   0.01370  -0.0949   0.3459   0.6294
   9.250   1.1900   0.02044   0.01434  -0.0912   0.3225   0.6395
   9.500   1.1939   0.02126   0.01511  -0.0876   0.2975   0.6506
   9.750   1.1961   0.02227   0.01604  -0.0841   0.2731   0.6628
  10.000   1.1969   0.02341   0.01714  -0.0806   0.2493   0.6740
  10.250   1.1960   0.02475   0.01841  -0.0772   0.2282   0.6859
  10.500   1.1973   0.02613   0.01977  -0.0744   0.2078   0.6992
  10.750   1.1978   0.02767   0.02127  -0.0717   0.1894   0.7136
  11.000   1.1983   0.02931   0.02290  -0.0693   0.1728   0.7287
  11.250   1.1987   0.03103   0.02463  -0.0670   0.1581   0.7447
  11.500   1.1991   0.03284   0.02646  -0.0649   0.1448   0.7625
  11.750   1.1987   0.03478   0.02842  -0.0630   0.1331   0.7822
  12.000   1.1975   0.03681   0.03049  -0.0611   0.1226   0.8063
  12.250   1.1980   0.03857   0.03236  -0.0591   0.1129   0.8402
  12.500   1.1862   0.04023   0.03415  -0.0555   0.1068   1.0000
  12.750   1.1929   0.04252   0.03644  -0.0555   0.0975   1.0000
  13.000   1.1961   0.04507   0.03894  -0.0552   0.0900   1.0000
  13.250   1.1977   0.04778   0.04160  -0.0550   0.0833   1.0000
  13.500   1.2012   0.05037   0.04420  -0.0547   0.0770   1.0000
  13.750   1.2023   0.05324   0.04703  -0.0546   0.0716   1.0000
  14.000   1.2048   0.05605   0.04985  -0.0545   0.0665   1.0000
  14.250   1.2076   0.05888   0.05270  -0.0546   0.0621   1.0000
  14.500   1.2068   0.06212   0.05589  -0.0546   0.0582   1.0000
  14.750   1.2113   0.06494   0.05879  -0.0549   0.0543   1.0000
  15.000   1.2122   0.06816   0.06199  -0.0552   0.0512   1.0000
  15.250   1.2142   0.07129   0.06514  -0.0555   0.0481   1.0000
  15.500   1.2174   0.07441   0.06834  -0.0560   0.0452   1.0000
  15.750   1.2189   0.07771   0.07163  -0.0566   0.0430   1.0000
  16.000   1.2214   0.08089   0.07482  -0.0569   0.0407   1.0000
  16.250   1.2245   0.08418   0.07821  -0.0577   0.0386   1.0000
  16.500   1.2272   0.08749   0.08154  -0.0585   0.0368   1.0000
  16.750   1.2305   0.09058   0.08457  -0.0590   0.0352   1.0000
  17.000   1.2340   0.09385   0.08794  -0.0597   0.0337   1.0000
  17.250   1.2370   0.09726   0.09146  -0.0606   0.0324   1.0000
  17.500   1.2400   0.10065   0.09491  -0.0617   0.0311   1.0000
  17.750   1.2439   0.10382   0.09807  -0.0626   0.0301   1.0000
  18.000   1.2526   0.10602   0.10019  -0.0627   0.0289   1.0000
  18.250   1.2518   0.11020   0.10456  -0.0644   0.0281   1.0000
  18.500   1.2522   0.11417   0.10867  -0.0660   0.0272   1.0000
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