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NREL's S818 Airfoil (s818-nr) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NREL's S818 Airfoil (s818-nr)
Reynolds number: 100,000
Max Cl/Cd: 39.56 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s818-nr-100000-n5.txt
Download as CSV file: xf-s818-nr-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S818 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3519   0.11340   0.10638  -0.0283   1.0000   0.3419
 -10.500  -0.3406   0.11259   0.10555  -0.0273   1.0000   0.3457
 -10.250  -0.3441   0.11186   0.10481  -0.0261   1.0000   0.3542
 -10.000  -0.3262   0.11101   0.10395  -0.0251   1.0000   0.3563
  -9.750  -0.3147   0.11012   0.10305  -0.0239   1.0000   0.3588
  -9.500  -0.3156   0.10958   0.10250  -0.0230   0.9996   0.3662
  -9.250  -0.2874   0.10986   0.10273  -0.0261   0.9952   0.3834
  -9.000  -0.2778   0.10774   0.10052  -0.0298   0.9903   0.3840
  -8.750  -0.2354   0.10476   0.09747  -0.0331   0.9860   0.3852
  -8.500  -0.1943   0.10242   0.09507  -0.0366   0.9822   0.3870
  -8.250  -0.1645   0.10028   0.09287  -0.0396   0.9770   0.3883
  -8.000  -0.1361   0.09821   0.09075  -0.0426   0.9714   0.3898
  -7.750  -0.1066   0.09647   0.08895  -0.0458   0.9666   0.3938
  -7.500  -0.1066   0.09552   0.08797  -0.0474   0.9570   0.3994
  -7.250  -0.1179   0.09144   0.08379  -0.0499   0.9461   0.3839
  -6.000  -0.0083   0.08109   0.07334  -0.0543   0.8810   0.3752
  -5.750   0.0066   0.07880   0.07100  -0.0559   0.8662   0.3735
  -5.500   0.0215   0.07630   0.06843  -0.0582   0.8515   0.3718
  -5.250   0.0413   0.07377   0.06581  -0.0612   0.8366   0.3709
  -5.000   0.0780   0.07164   0.06357  -0.0655   0.8209   0.3715
  -4.750   0.1203   0.06931   0.06110  -0.0712   0.8034   0.3720
  -4.500   0.1590   0.06652   0.05811  -0.0782   0.7835   0.3712
  -4.250   0.1899   0.06400   0.05539  -0.0837   0.7606   0.3704
  -4.000   0.2136   0.06199   0.05319  -0.0871   0.7374   0.3700
  -3.750   0.2331   0.06024   0.05127  -0.0893   0.7160   0.3697
  -3.500   0.2507   0.05875   0.04964  -0.0906   0.6973   0.3697
  -3.250   0.2669   0.05743   0.04820  -0.0914   0.6800   0.3698
  -3.000   0.2829   0.05625   0.04692  -0.0917   0.6643   0.3699
  -2.750   0.3018   0.05539   0.04598  -0.0918   0.6498   0.3705
  -2.500   0.3204   0.05462   0.04514  -0.0917   0.6367   0.3712
  -2.250   0.3356   0.05371   0.04414  -0.0915   0.6251   0.3717
  -2.000   0.3441   0.05267   0.04307  -0.0905   0.6138   0.3720
  -1.750   0.3513   0.05154   0.04189  -0.0894   0.6042   0.3722
  -1.500   0.3560   0.05041   0.04071  -0.0880   0.5952   0.3723
  -1.250   0.3606   0.04936   0.03962  -0.0864   0.5872   0.3728
  -1.000   0.3623   0.04831   0.03857  -0.0843   0.5796   0.3732
   0.000   0.3247   0.03401   0.02379  -0.0906   0.5579   0.3846
   0.250   0.3470   0.03352   0.02330  -0.0907   0.5515   0.3852
   0.500   0.3702   0.03304   0.02281  -0.0911   0.5455   0.3860
   0.750   0.3965   0.03255   0.02228  -0.0920   0.5405   0.3869
   1.000   0.4205   0.03202   0.02174  -0.0927   0.5350   0.3880
   1.250   0.4454   0.03146   0.02118  -0.0936   0.5294   0.3892
   1.500   0.4733   0.03085   0.02051  -0.0952   0.5247   0.3906
   1.750   0.5028   0.03015   0.01974  -0.0973   0.5202   0.3924
   2.000   0.5321   0.02934   0.01889  -0.0997   0.5152   0.3946
   2.250   0.5667   0.02842   0.01784  -0.1033   0.5109   0.3975
   2.500   0.6049   0.02761   0.01684  -0.1074   0.5073   0.4006
   2.750   0.6331   0.02770   0.01697  -0.1078   0.5041   0.4016
   3.000   0.6577   0.02779   0.01719  -0.1076   0.5002   0.4027
   3.250   0.6841   0.02788   0.01737  -0.1078   0.4966   0.4039
   3.500   0.7120   0.02793   0.01747  -0.1083   0.4932   0.4053
   3.750   0.7423   0.02794   0.01748  -0.1093   0.4901   0.4070
   4.000   0.7739   0.02794   0.01747  -0.1107   0.4873   0.4087
   4.250   0.8002   0.02795   0.01757  -0.1112   0.4838   0.4107
   4.500   0.8294   0.02795   0.01761  -0.1124   0.4806   0.4129
   4.750   0.8611   0.02793   0.01759  -0.1140   0.4778   0.4153
   5.000   0.8921   0.02800   0.01768  -0.1153   0.4752   0.4173
   5.250   0.9205   0.02823   0.01800  -0.1157   0.4730   0.4186
   5.500   0.9509   0.02847   0.01831  -0.1164   0.4709   0.4201
   5.750   0.9718   0.02881   0.01884  -0.1157   0.4678   0.4217
   6.000   0.9941   0.02915   0.01934  -0.1152   0.4647   0.4237
   6.250   1.0190   0.02949   0.01981  -0.1152   0.4620   0.4262
   6.500   1.0464   0.02979   0.02020  -0.1157   0.4596   0.4290
   6.750   1.0773   0.03005   0.02047  -0.1169   0.4573   0.4324
   7.000   1.1075   0.03032   0.02083  -0.1177   0.4550   0.4346
   7.250   1.1320   0.03075   0.02141  -0.1175   0.4526   0.4365
   7.500   1.1465   0.03134   0.02226  -0.1157   0.4493   0.4384
   7.750   1.1647   0.03185   0.02295  -0.1146   0.4457   0.4406
   8.000   1.1878   0.03223   0.02347  -0.1143   0.4423   0.4431
   8.250   1.2172   0.03249   0.02378  -0.1149   0.4393   0.4462
   8.500   1.2514   0.03269   0.02396  -0.1164   0.4362   0.4499
   8.750   1.2522   0.03348   0.02507  -0.1125   0.4311   0.4515
   9.000   1.2675   0.03371   0.02547  -0.1106   0.4251   0.4538
   9.250   1.2959   0.03341   0.02519  -0.1105   0.4180   0.4570
   9.500   1.2911   0.03394   0.02593  -0.1057   0.4108   0.4594
   9.750   1.3241   0.03347   0.02539  -0.1063   0.4034   0.4639
  10.000   1.3189   0.03439   0.02652  -0.1019   0.3972   0.4666
  10.250   1.3289   0.03480   0.02711  -0.0995   0.3908   0.4690
  10.500   1.3481   0.03490   0.02730  -0.0982   0.3846   0.4720
  10.750   1.3405   0.03613   0.02879  -0.0940   0.3778   0.4742
  11.000   1.3597   0.03615   0.02885  -0.0929   0.3704   0.4779
  11.250   1.3493   0.03777   0.03070  -0.0890   0.3632   0.4803
  11.500   1.3563   0.03850   0.03151  -0.0870   0.3548   0.4841
  11.750   1.3438   0.04058   0.03384  -0.0837   0.3468   0.4859
  12.000   1.3440   0.04191   0.03531  -0.0816   0.3375   0.4886
  12.250   1.3165   0.04584   0.03951  -0.0788   0.3284   0.4900
  12.500   1.3017   0.04912   0.04296  -0.0773   0.3181   0.4923
  12.750   1.2640   0.05538   0.04940  -0.0765   0.3073   0.4931
  13.000   1.2049   0.06535   0.05955  -0.0775   0.2944   0.4920
  13.250   1.1815   0.07146   0.06576  -0.0785   0.2785   0.4934
  13.500   1.1909   0.07318   0.06747  -0.0786   0.2612   0.4978
  13.750   1.2082   0.07367   0.06785  -0.0783   0.2400   0.5026
  14.000   1.2118   0.07595   0.07002  -0.0782   0.2187   0.5059
  14.250   1.2064   0.07964   0.07359  -0.0787   0.1997   0.5089
  14.500   1.1981   0.08394   0.07779  -0.0795   0.1829   0.5119
  14.750   1.1902   0.08840   0.08217  -0.0805   0.1679   0.5151
  15.000   1.1836   0.09282   0.08654  -0.0817   0.1542   0.5184
  15.250   1.1787   0.09703   0.09075  -0.0829   0.1420   0.5210
  15.500   1.1757   0.10105   0.09477  -0.0840   0.1312   0.5242
  15.750   1.1736   0.10496   0.09865  -0.0853   0.1218   0.5280
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