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NREL's S828 Airfoil (s828-nr) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NREL's S828 Airfoil (s828-nr)
Reynolds number: 200,000
Max Cl/Cd: 40.32 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s828-nr-200000-n5.txt
Download as CSV file: xf-s828-nr-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S828 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.2893   0.09275   0.08869  -0.1011   0.8614   0.0074
 -12.000  -0.2989   0.08653   0.08248  -0.1039   0.8577   0.0071
 -11.750  -0.3176   0.07754   0.07353  -0.1087   0.8536   0.0072
 -11.500  -0.3516   0.06527   0.06113  -0.1160   0.8494   0.0067
 -11.250  -0.3846   0.05826   0.05391  -0.1174   0.8455   0.0066
 -11.000  -0.4301   0.05078   0.04607  -0.1155   0.8405   0.0062
 -10.750  -0.4557   0.04611   0.04100  -0.1122   0.8363   0.0059
 -10.500  -0.4678   0.04348   0.03808  -0.1090   0.8330   0.0059
 -10.250  -0.4846   0.04040   0.03470  -0.1049   0.8294   0.0060
 -10.000  -0.4922   0.03817   0.03223  -0.1013   0.8257   0.0061
  -9.750  -0.4958   0.03572   0.02940  -0.0976   0.8226   0.0060
  -9.500  -0.4971   0.03369   0.02711  -0.0942   0.8199   0.0062
  -9.000  -0.4828   0.03027   0.02313  -0.0890   0.8148   0.0065
  -8.750  -0.4699   0.02877   0.02138  -0.0872   0.8121   0.0068
  -8.500  -0.4505   0.02706   0.01938  -0.0863   0.8100   0.0070
  -8.250  -0.4279   0.02556   0.01762  -0.0859   0.8083   0.0072
  -8.000  -0.4051   0.02451   0.01633  -0.0855   0.8067   0.0081
  -7.750  -0.3826   0.02352   0.01517  -0.0852   0.8052   0.0096
  -7.500  -0.3598   0.02267   0.01421  -0.0848   0.8039   0.0102
  -7.250  -0.3364   0.02176   0.01319  -0.0845   0.8023   0.0111
  -7.000  -0.3146   0.02088   0.01221  -0.0838   0.8005   0.0117
  -6.750  -0.2947   0.02010   0.01131  -0.0827   0.7987   0.0129
  -6.500  -0.2767   0.01933   0.01049  -0.0815   0.7969   0.0145
  -6.250  -0.2568   0.01884   0.00992  -0.0804   0.7953   0.0171
  -6.000  -0.2381   0.01825   0.00930  -0.0792   0.7938   0.0235
  -5.750  -0.2195   0.01769   0.00874  -0.0779   0.7923   0.0328
  -5.500  -0.2010   0.01719   0.00828  -0.0765   0.7909   0.0504
  -5.250  -0.1831   0.01672   0.00791  -0.0752   0.7896   0.0780
  -5.000  -0.1683   0.01629   0.00768  -0.0733   0.7878   0.1191
  -4.750  -0.1558   0.01586   0.00748  -0.0710   0.7860   0.1733
  -4.500  -0.1485   0.01537   0.00731  -0.0678   0.7841   0.2491
  -4.250  -0.1495   0.01481   0.00718  -0.0627   0.7821   0.3467
  -4.000  -0.1563   0.01412   0.00703  -0.0564   0.7801   0.4673
  -3.750  -0.0538   0.01537   0.00936  -0.0682   0.7813   0.7457
  -3.500  -0.0424   0.01557   0.00948  -0.0650   0.7798   0.7694
  -3.250  -0.0461   0.01555   0.00939  -0.0591   0.7781   0.7899
  -3.000  -0.0317   0.01595   0.00970  -0.0561   0.7769   0.8044
  -2.750   0.0089   0.01667   0.01029  -0.0580   0.7763   0.8141
  -2.500   0.0564   0.01761   0.01111  -0.0610   0.7758   0.8268
  -2.250   0.0954   0.01821   0.01161  -0.0629   0.7751   0.8357
  -2.000   0.1109   0.01852   0.01191  -0.0607   0.7733   0.8439
  -1.750   0.1358   0.01872   0.01205  -0.0605   0.7718   0.8477
  -1.500   0.1673   0.01888   0.01215  -0.0617   0.7707   0.8497
  -1.000   0.1911   0.01913   0.01236  -0.0562   0.7673   0.8607
  -0.750   0.2231   0.01921   0.01238  -0.0575   0.7663   0.8620
  -0.500   0.2531   0.01925   0.01239  -0.0584   0.7652   0.8635
  -0.250   0.2802   0.01930   0.01240  -0.0587   0.7642   0.8656
   0.000   0.2687   0.01931   0.01239  -0.0512   0.7626   0.8741
   0.250   0.3011   0.01935   0.01241  -0.0526   0.7619   0.8750
   0.500   0.3289   0.01948   0.01254  -0.0532   0.7609   0.8762
   0.750   0.3396   0.01999   0.01312  -0.0506   0.7574   0.8788
   1.000   0.3426   0.02035   0.01350  -0.0462   0.7545   0.8830
   1.250   0.3292   0.02044   0.01360  -0.0384   0.7515   0.8894
   1.500   0.3568   0.02050   0.01366  -0.0389   0.7503   0.8905
   1.750   0.3844   0.02053   0.01371  -0.0393   0.7493   0.8917
   2.000   0.4113   0.02051   0.01369  -0.0396   0.7483   0.8929
   2.250   0.4374   0.02048   0.01368  -0.0396   0.7475   0.8944
   2.750   0.3906   0.02152   0.01482  -0.0209   0.7356   0.9059
   3.000   0.3851   0.02190   0.01523  -0.0151   0.7311   0.9095
   3.250   0.4383   0.02150   0.01486  -0.0202   0.7328   0.9086
   4.250   0.4092   0.02310   0.01660   0.0037   0.7078   0.9246
   4.750   0.4217   0.02356   0.01714   0.0102   0.6956   0.9307
   5.000   0.4561   0.02310   0.01675   0.0091   0.6941   0.9312
   5.250   0.4952   0.02235   0.01609   0.0073   0.6931   0.9314
   5.500   0.5305   0.02166   0.01547   0.0062   0.6904   0.9319
   6.000   0.5678   0.02125   0.01522   0.0091   0.6756   0.9356
   6.500   0.5789   0.02171   0.01584   0.0158   0.6536   0.9422
   7.500   0.6295   0.02279   0.01727   0.0231   0.5867   0.9515
   7.750   0.7246   0.01797   0.01204   0.0167   0.5029   0.9478
   8.000   0.7253   0.01874   0.01228   0.0208   0.4178   0.9511
   8.250   0.7151   0.02009   0.01328   0.0258   0.3548   0.9557
   8.500   0.7128   0.02148   0.01439   0.0290   0.2988   0.9587
   8.750   0.7151   0.02292   0.01557   0.0312   0.2439   0.9613
   9.000   0.7203   0.02425   0.01666   0.0330   0.1948   0.9639
   9.250   0.7279   0.02547   0.01769   0.0345   0.1526   0.9666
   9.500   0.7377   0.02656   0.01864   0.0358   0.1191   0.9694
   9.750   0.7515   0.02766   0.01962   0.0363   0.0920   0.9714
  10.000   0.7675   0.02876   0.02065   0.0364   0.0716   0.9732
  10.250   0.7840   0.02981   0.02170   0.0365   0.0579   0.9753
  10.500   0.7999   0.03090   0.02278   0.0366   0.0467   0.9775
  10.750   0.8143   0.03207   0.02394   0.0369   0.0393   0.9798
  11.000   0.8302   0.03311   0.02513   0.0372   0.0346   0.9824
  11.250   0.8434   0.03451   0.02654   0.0374   0.0297   0.9844
  11.500   0.8608   0.03559   0.02775   0.0372   0.0263   0.9867
  11.750   0.8755   0.03683   0.02907   0.0373   0.0232   0.9897
  12.000   0.8868   0.03829   0.03058   0.0377   0.0204   0.9936
  12.250   0.9013   0.03973   0.03217   0.0378   0.0186   0.9998
  12.500   0.9063   0.04070   0.03321   0.0398   0.0168   1.0000
  12.750   0.9103   0.04204   0.03457   0.0415   0.0150   1.0000
  13.000   0.9171   0.04344   0.03608   0.0430   0.0138   1.0000
  13.250   0.9261   0.04475   0.03754   0.0439   0.0118   1.0000
  13.500   0.9340   0.04620   0.03905   0.0447   0.0106   1.0000
  13.750   0.9402   0.04797   0.04093   0.0456   0.0093   1.0000
  14.000   0.9464   0.04981   0.04292   0.0465   0.0088   1.0000
  14.250   0.9522   0.05174   0.04500   0.0473   0.0084   1.0000
  14.500   0.9565   0.05386   0.04724   0.0479   0.0075   1.0000
  14.750   0.9604   0.05607   0.04957   0.0484   0.0071   1.0000
  15.000   0.9577   0.05906   0.05266   0.0491   0.0066   1.0000
  15.250   0.9593   0.06174   0.05552   0.0495   0.0065   1.0000
  15.500   0.9597   0.06469   0.05876   0.0498   0.0057   1.0000
  15.750   0.9580   0.06791   0.06217   0.0499   0.0058   1.0000
  16.000   0.9523   0.07177   0.06625   0.0498   0.0057   1.0000
  16.250   0.9495   0.07526   0.06993   0.0491   0.0052   1.0000
  16.500   0.9405   0.07986   0.07474   0.0483   0.0051   1.0000
  16.750   0.9400   0.08322   0.07819   0.0468   0.0047   1.0000
  17.000   0.9215   0.08976   0.08503   0.0452   0.0049   1.0000
  17.250   0.9235   0.09300   0.08827   0.0430   0.0044   1.0000
  17.500   0.9064   0.09984   0.09542   0.0405   0.0046   1.0000
  17.750   0.8806   0.10880   0.10465   0.0366   0.0047   1.0000
  18.000   0.8810   0.11293   0.10874   0.0334   0.0041   1.0000
  18.250   0.8524   0.12355   0.11969   0.0282   0.0046   1.0000
  18.500   0.8091   0.13904   0.13552   0.0199   0.0050   1.0000
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