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NREL's S826 Airfoil (s826-nr) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NREL's S826 Airfoil (s826-nr)
Reynolds number: 100,000
Max Cl/Cd: 60.86 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s826-nr-100000.txt
Download as CSV file: xf-s826-nr-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S826 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3634   0.11434   0.10974  -0.0423   1.0000   0.0929
  -9.250  -0.3916   0.11175   0.10730  -0.0455   1.0000   0.0942
  -9.000  -0.4179   0.10881   0.10449  -0.0476   1.0000   0.0946
  -8.750  -0.3700   0.10518   0.10078  -0.0403   1.0000   0.0991
  -8.500  -0.3723   0.10284   0.09848  -0.0392   1.0000   0.1026
  -8.250  -0.3868   0.10021   0.09596  -0.0392   1.0000   0.1061
  -8.000  -0.4201   0.09768   0.09360  -0.0404   1.0000   0.1081
  -7.750  -0.4587   0.09530   0.09138  -0.0403   1.0000   0.1086
  -7.500  -0.4321   0.09243   0.08851  -0.0358   1.0000   0.1125
  -7.250  -0.4370   0.09088   0.08702  -0.0330   1.0000   0.1154
  -7.000  -0.4578   0.08924   0.08550  -0.0306   1.0000   0.1177
  -6.500  -0.4922   0.07565   0.07200  -0.0507   0.9900   0.1265
  -6.250  -0.4704   0.06759   0.06372  -0.0658   0.9790   0.1409
  -6.000  -0.4425   0.06326   0.05939  -0.0702   0.9722   0.1576
  -5.750  -0.4186   0.05983   0.05598  -0.0730   0.9630   0.1768
  -5.500  -0.3272   0.04224   0.03553  -0.0979   0.9596   0.0553
  -5.250  -0.2854   0.03984   0.03258  -0.1011   0.9517   0.0533
  -5.000  -0.2410   0.03610   0.02844  -0.1052   0.9472   0.0527
  -4.750  -0.2011   0.03312   0.02512  -0.1077   0.9411   0.0522
  -4.500  -0.1595   0.03108   0.02274  -0.1098   0.9349   0.0538
  -4.250  -0.1233   0.02904   0.02080  -0.1117   0.9290   0.0625
  -4.000  -0.0881   0.02749   0.01938  -0.1126   0.9220   0.0735
  -3.750  -0.0508   0.02641   0.01841  -0.1142   0.9149   0.0951
  -3.500   0.0123   0.02443   0.01790  -0.1230   0.9102   0.4728
  -3.250   0.0264   0.02680   0.02041  -0.1166   0.8985   0.5152
  -3.000   0.0477   0.02854   0.02220  -0.1113   0.8918   0.5449
  -2.750   0.0642   0.02940   0.02300  -0.1076   0.8806   0.5650
  -2.500   0.0832   0.02998   0.02350  -0.1043   0.8713   0.5805
  -2.250   0.1091   0.03029   0.02374  -0.1018   0.8653   0.5965
  -2.000   0.1335   0.03037   0.02371  -0.1009   0.8560   0.6098
  -1.750   0.1657   0.03008   0.02332  -0.1007   0.8511   0.6176
  -1.500   0.2065   0.02947   0.02251  -0.1047   0.8447   0.6201
  -1.250   0.2505   0.02876   0.02161  -0.1092   0.8389   0.6212
  -1.000   0.3043   0.02779   0.02043  -0.1154   0.8362   0.6229
  -0.750   0.3382   0.02742   0.01996  -0.1173   0.8291   0.6249
  -0.500   0.3766   0.02694   0.01940  -0.1196   0.8238   0.6274
  -0.250   0.4262   0.02625   0.01861  -0.1240   0.8212   0.6303
   0.000   0.4574   0.02617   0.01846  -0.1258   0.8135   0.6329
   0.250   0.5039   0.02568   0.01786  -0.1303   0.8090   0.6365
   0.500   0.5522   0.02506   0.01718  -0.1345   0.8060   0.6402
   0.750   0.5729   0.02532   0.01745  -0.1339   0.7970   0.6432
   1.000   0.6148   0.02499   0.01709  -0.1369   0.7929   0.6470
   1.250   0.6648   0.02449   0.01653  -0.1417   0.7901   0.6516
   1.500   0.6806   0.02504   0.01711  -0.1406   0.7805   0.6550
   1.750   0.7202   0.02476   0.01685  -0.1427   0.7767   0.6593
   2.000   0.7404   0.02531   0.01745  -0.1424   0.7690   0.6635
   2.250   0.7792   0.02525   0.01737  -0.1452   0.7639   0.6684
   2.500   0.8189   0.02497   0.01714  -0.1473   0.7606   0.6726
   2.750   0.8295   0.02587   0.01813  -0.1452   0.7514   0.6770
   3.000   0.8721   0.02567   0.01796  -0.1483   0.7472   0.6834
   3.250   0.8862   0.02639   0.01880  -0.1465   0.7393   0.6875
   3.500   0.9202   0.02641   0.01889  -0.1479   0.7339   0.6930
   3.750   0.9545   0.02651   0.01907  -0.1494   0.7285   0.6991
   4.000   0.9724   0.02709   0.01979  -0.1482   0.7204   0.7044
   4.250   1.0200   0.02660   0.01934  -0.1514   0.7159   0.7127
   4.500   1.0292   0.02745   0.02038  -0.1487   0.7058   0.7179
   4.750   1.0724   0.02697   0.01998  -0.1510   0.6994   0.7262
   5.000   1.0938   0.02721   0.02037  -0.1499   0.6893   0.7325
   5.250   1.1217   0.02726   0.02057  -0.1498   0.6793   0.7412
   5.500   1.1665   0.02636   0.01974  -0.1516   0.6706   0.7505
   5.750   1.1878   0.02653   0.02008  -0.1504   0.6587   0.7597
   6.000   1.2131   0.02648   0.02018  -0.1496   0.6467   0.7700
   6.250   1.2410   0.02619   0.02005  -0.1489   0.6344   0.7803
   6.500   1.2704   0.02580   0.01979  -0.1485   0.6214   0.7923
   6.750   1.2977   0.02540   0.01953  -0.1476   0.6072   0.8059
   7.000   1.3214   0.02502   0.01933  -0.1461   0.5914   0.8213
   7.250   1.3429   0.02460   0.01907  -0.1442   0.5741   0.8392
   7.500   1.3631   0.02407   0.01869  -0.1419   0.5552   0.8615
   7.750   1.3784   0.02347   0.01824  -0.1387   0.5354   0.8952
   8.000   1.3901   0.02312   0.01810  -0.1354   0.5101   1.0000
   8.250   1.4071   0.02312   0.01818  -0.1336   0.4753   1.0000
   8.500   1.4116   0.02346   0.01851  -0.1296   0.4279   1.0000
   8.750   1.4068   0.02426   0.01892  -0.1239   0.3634   1.0000
   9.000   1.3952   0.02608   0.02017  -0.1180   0.3038   1.0000
   9.250   1.3838   0.02833   0.02199  -0.1128   0.2571   1.0000
   9.500   1.3751   0.03071   0.02406  -0.1084   0.2202   1.0000
   9.750   1.3692   0.03313   0.02623  -0.1047   0.1914   1.0000
  10.000   1.3663   0.03556   0.02846  -0.1016   0.1675   1.0000
  10.250   1.3658   0.03797   0.03070  -0.0990   0.1475   1.0000
  10.500   1.3680   0.04042   0.03296  -0.0968   0.1303   1.0000
  10.750   1.3720   0.04278   0.03530  -0.0948   0.1148   1.0000
  11.000   1.3770   0.04519   0.03768  -0.0931   0.1012   1.0000
  11.250   1.3831   0.04767   0.04014  -0.0915   0.0889   1.0000
  11.500   1.3898   0.05024   0.04264  -0.0901   0.0774   1.0000
  11.750   1.3923   0.05281   0.04535  -0.0887   0.0685   1.0000
  12.000   1.4003   0.05562   0.04828  -0.0873   0.0596   1.0000
  12.250   1.4109   0.05853   0.05120  -0.0862   0.0521   1.0000
  12.500   1.4186   0.06139   0.05422  -0.0850   0.0467   1.0000
  12.750   1.4285   0.06485   0.05781  -0.0840   0.0417   1.0000
  13.000   1.4312   0.06824   0.06149  -0.0828   0.0386   1.0000
  13.250   1.4368   0.07168   0.06508  -0.0820   0.0362   1.0000
  13.500   1.4418   0.07663   0.07020  -0.0813   0.0339   1.0000
  13.750   1.4281   0.08102   0.07502  -0.0806   0.0331   1.0000
  14.000   1.4144   0.08582   0.08019  -0.0804   0.0322   1.0000
  14.250   1.3998   0.09101   0.08572  -0.0808   0.0316   1.0000
  14.500   1.3836   0.09660   0.09162  -0.0817   0.0311   1.0000
  14.750   1.3660   0.10269   0.09801  -0.0833   0.0309   1.0000
  15.000   1.3469   0.10931   0.10493  -0.0857   0.0310   1.0000
  15.250   1.3259   0.11655   0.11244  -0.0889   0.0311   1.0000
  15.500   1.3040   0.12440   0.12054  -0.0930   0.0314   1.0000
  15.750   1.2823   0.13281   0.12915  -0.0979   0.0320   1.0000
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