Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NREL's S827 Airfoil (s827-nr) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NREL's S827 Airfoil (s827-nr)
Reynolds number: 500,000
Max Cl/Cd: 84.44 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s827-nr-500000.txt
Download as CSV file: xf-s827-nr-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S827 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.1586   0.08967   0.08668  -0.1256   0.8297   0.0149
 -13.250  -0.2744   0.07876   0.07539  -0.1424   0.8450   0.0136
 -13.000  -0.2890   0.07488   0.07141  -0.1427   0.8414   0.0136
 -12.750  -0.3101   0.07056   0.06699  -0.1425   0.8381   0.0137
 -12.500  -0.3272   0.06698   0.06329  -0.1419   0.8349   0.0138
 -12.250  -0.3441   0.06364   0.05981  -0.1409   0.8319   0.0138
 -12.000  -0.3570   0.06076   0.05687  -0.1398   0.8290   0.0140
 -11.750  -0.3686   0.05816   0.05418  -0.1383   0.8259   0.0141
 -11.500  -0.3796   0.05568   0.05159  -0.1366   0.8230   0.0142
 -11.250  -0.3900   0.05353   0.04933  -0.1347   0.8203   0.0144
 -11.000  -0.3976   0.05149   0.04714  -0.1327   0.8178   0.0145
 -10.750  -0.4060   0.04951   0.04509  -0.1304   0.8153   0.0147
 -10.500  -0.4121   0.04757   0.04305  -0.1279   0.8127   0.0149
 -10.250  -0.4162   0.04571   0.04106  -0.1253   0.8103   0.0151
 -10.000  -0.4192   0.04388   0.03910  -0.1225   0.8081   0.0155
  -9.750  -0.4203   0.04202   0.03709  -0.1196   0.8061   0.0160
  -9.500  -0.4178   0.04025   0.03513  -0.1167   0.8042   0.0167
  -9.250  -0.3203   0.02911   0.02277  -0.1219   0.8054   0.0095
  -9.000  -0.2345   0.02771   0.02114  -0.1258   0.8056   0.0080
  -8.750  -0.1898   0.02795   0.02119  -0.1256   0.8046   0.0079
  -8.500  -0.1662   0.02792   0.02109  -0.1245   0.8032   0.0080
  -8.250  -0.1486   0.02763   0.02078  -0.1232   0.8016   0.0079
  -8.000  -0.1343   0.02717   0.02030  -0.1219   0.7999   0.0081
  -7.750  -0.1224   0.02656   0.01966  -0.1204   0.7983   0.0088
  -7.500  -0.1115   0.02588   0.01895  -0.1190   0.7968   0.0086
  -7.250  -0.1086   0.02487   0.01792  -0.1166   0.7951   0.0101
  -7.000  -0.1001   0.02405   0.01709  -0.1150   0.7937   0.0124
  -6.750  -0.0972   0.02299   0.01598  -0.1128   0.7923   0.0144
  -6.500  -0.0975   0.02179   0.01479  -0.1102   0.7908   0.0225
  -6.250  -0.0988   0.02055   0.01359  -0.1076   0.7894   0.0336
  -6.000  -0.1016   0.01925   0.01238  -0.1047   0.7880   0.0519
  -5.750  -0.1054   0.01793   0.01115  -0.1017   0.7864   0.0748
  -5.500  -0.1140   0.01645   0.00979  -0.0980   0.7846   0.1065
  -5.250  -0.1270   0.01499   0.00845  -0.0934   0.7826   0.1455
  -5.000  -0.1519   0.01396   0.00753  -0.0860   0.7805   0.1924
  -4.750  -0.1794   0.01219   0.00617  -0.0782   0.7788   0.3394
  -4.500  -0.1785   0.01125   0.00580  -0.0746   0.7777   0.5195
  -4.250  -0.1521   0.01158   0.00602  -0.0748   0.7769   0.5421
  -4.000  -0.1243   0.01190   0.00632  -0.0751   0.7762   0.5518
  -3.750  -0.0974   0.01221   0.00660  -0.0754   0.7754   0.5597
  -3.500  -0.0710   0.01265   0.00702  -0.0754   0.7747   0.5680
  -3.250  -0.0450   0.01282   0.00717  -0.0755   0.7739   0.5723
  -3.000  -0.0175   0.01315   0.00754  -0.0758   0.7730   0.5766
  -2.750   0.0087   0.01361   0.00797  -0.0758   0.7721   0.5830
  -2.500   0.0344   0.01366   0.00796  -0.0760   0.7711   0.5847
  -2.250   0.0604   0.01359   0.00786  -0.0763   0.7700   0.5853
  -2.000   0.0866   0.01358   0.00783  -0.0767   0.7691   0.5859
  -1.750   0.1129   0.01359   0.00782  -0.0770   0.7682   0.5866
  -1.500   0.1394   0.01362   0.00783  -0.0774   0.7674   0.5872
  -1.250   0.1660   0.01365   0.00785  -0.0778   0.7667   0.5878
  -1.000   0.1927   0.01369   0.00788  -0.0782   0.7659   0.5885
  -0.750   0.2196   0.01375   0.00792  -0.0787   0.7653   0.5891
  -0.500   0.2466   0.01381   0.00797  -0.0792   0.7646   0.5899
  -0.250   0.2744   0.01385   0.00800  -0.0798   0.7639   0.5907
   0.000   0.3025   0.01390   0.00805  -0.0805   0.7632   0.5915
   0.250   0.3301   0.01400   0.00814  -0.0810   0.7625   0.5924
   0.500   0.3572   0.01416   0.00829  -0.0816   0.7619   0.5933
   0.750   0.3759   0.01444   0.00861  -0.0805   0.7607   0.5942
   1.000   0.3868   0.01485   0.00908  -0.0780   0.7582   0.5952
   1.250   0.4012   0.01523   0.00949  -0.0761   0.7560   0.5961
   1.500   0.4222   0.01545   0.00971  -0.0755   0.7543   0.5970
   1.750   0.4469   0.01559   0.00986  -0.0755   0.7530   0.5979
   2.000   0.4738   0.01567   0.00995  -0.0760   0.7520   0.5988
   2.250   0.5010   0.01570   0.01003  -0.0765   0.7510   0.5999
   2.500   0.5292   0.01575   0.01013  -0.0771   0.7502   0.6011
   2.750   0.5584   0.01581   0.01024  -0.0780   0.7494   0.6023
   3.000   0.5891   0.01587   0.01035  -0.0791   0.7487   0.6034
   3.250   0.6205   0.01595   0.01048  -0.0804   0.7480   0.6046
   3.500   0.4888   0.01978   0.01435  -0.0519   0.7288   0.6053
   3.750   0.5314   0.01928   0.01392  -0.0549   0.7294   0.6066
   4.000   0.5750   0.01879   0.01347  -0.0582   0.7299   0.6079
   4.250   0.6210   0.01824   0.01299  -0.0618   0.7302   0.6093
   4.500   0.6711   0.01760   0.01240  -0.0663   0.7299   0.6107
   4.750   0.7889   0.01485   0.00967  -0.0829   0.7296   0.6123
   5.000   0.8485   0.01324   0.00804  -0.0887   0.7222   0.6138
   5.250   0.8805   0.01282   0.00769  -0.0897   0.7172   0.6152
   5.500   0.8993   0.01260   0.00758  -0.0881   0.7112   0.6166
   5.750   0.9386   0.01200   0.00700  -0.0904   0.7046   0.6182
   6.000   0.9459   0.01193   0.00704  -0.0866   0.6974   0.6197
   6.250   0.9650   0.01160   0.00675  -0.0849   0.6886   0.6215
   6.500   0.9677   0.01146   0.00667  -0.0799   0.6798   0.6233
   6.750   0.9666   0.01162   0.00691  -0.0745   0.6702   0.6250
   7.000   0.9685   0.01184   0.00720  -0.0699   0.6575   0.6266
   7.250   0.9675   0.01212   0.00752  -0.0648   0.6361   0.6282
   7.500   0.9581   0.01264   0.00782  -0.0582   0.5783   0.6299
   7.750   0.9339   0.01410   0.00894  -0.0497   0.5211   0.6314
   8.000   0.9084   0.01598   0.01053  -0.0418   0.4670   0.6329
   8.250   0.8874   0.01795   0.01225  -0.0350   0.4143   0.6346
   8.500   0.8697   0.01999   0.01400  -0.0292   0.3583   0.6363
   8.750   0.8578   0.02192   0.01562  -0.0245   0.3013   0.6381
   9.000   0.8510   0.02369   0.01708  -0.0207   0.2443   0.6400
   9.250   0.8484   0.02533   0.01841  -0.0175   0.1892   0.6417
   9.500   0.8513   0.02668   0.01954  -0.0151   0.1434   0.6438
   9.750   0.8568   0.02796   0.02065  -0.0131   0.1068   0.6460
  10.000   0.8652   0.02911   0.02167  -0.0115   0.0792   0.6483
  10.250   0.8743   0.03026   0.02272  -0.0100   0.0576   0.6508
  10.500   0.8854   0.03134   0.02375  -0.0088   0.0439   0.6536
  10.750   0.8963   0.03246   0.02483  -0.0076   0.0347   0.6563
  11.000   0.9086   0.03347   0.02587  -0.0066   0.0282   0.6592
  11.250   0.9216   0.03447   0.02694  -0.0056   0.0234   0.6620
  11.500   0.9306   0.03579   0.02827  -0.0044   0.0193   0.6651
  11.750   0.9452   0.03673   0.02927  -0.0037   0.0163   0.6684
  12.000   0.9518   0.03830   0.03086  -0.0023   0.0130   0.6714
  12.250   0.9661   0.03929   0.03197  -0.0017   0.0110   0.6748
  12.500   0.9764   0.04061   0.03336  -0.0007   0.0097   0.6783
  12.750   0.9877   0.04188   0.03469   0.0000   0.0076   0.6822
  13.000   0.9983   0.04325   0.03614   0.0008   0.0073   0.6860
  13.250   1.0080   0.04468   0.03766   0.0016   0.0064   0.6897
  13.500   1.0084   0.04702   0.04012   0.0033   0.0056   0.6934
  13.750   1.0217   0.04823   0.04142   0.0036   0.0053   0.6981
  14.000   1.0295   0.04996   0.04328   0.0044   0.0049   0.7022
  14.250   1.0370   0.05175   0.04519   0.0051   0.0046   0.7066
  14.500   1.0458   0.05347   0.04700   0.0056   0.0043   0.7119
  14.750   1.0508   0.05561   0.04929   0.0063   0.0043   0.7165
  15.000   1.0559   0.05775   0.05156   0.0069   0.0041   0.7214
  15.250   1.0562   0.06051   0.05446   0.0077   0.0039   0.7264
  15.500   1.0554   0.06353   0.05767   0.0085   0.0037   0.7309
  15.750   1.0606   0.06587   0.06020   0.0087   0.0036   0.7366
  16.000   1.0648   0.06841   0.06291   0.0088   0.0033   0.7427
  16.250   1.0656   0.07137   0.06607   0.0090   0.0033   0.7481
  16.500   1.0649   0.07463   0.06953   0.0090   0.0031   0.7540
  16.750   1.0637   0.07802   0.07309   0.0087   0.0029   0.7599
  17.000   1.0560   0.08246   0.07779   0.0084   0.0030   0.7653
  17.500   1.0405   0.09169   0.08746   0.0067   0.0030   0.7771
  17.750   1.0295   0.09705   0.09305   0.0052   0.0030   0.7832
  18.000   1.0191   0.10250   0.09870   0.0033   0.0030   0.7895
  18.250   1.0111   0.10772   0.10409   0.0010   0.0028   0.7972
  18.500   1.0002   0.11362   0.11018  -0.0017   0.0027   0.8046
  18.750   0.9751   0.12248   0.11934  -0.0057   0.0029   0.8092
  19.000   0.9641   0.12895   0.12598  -0.0094   0.0027   0.8176
<< Back to NREL's S827 Airfoil (s827-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S827 Airfoil (s827-nr)