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NREL's S804 Airfoil (s804-nr) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NREL's S804 Airfoil (s804-nr)
Reynolds number: 100,000
Max Cl/Cd: 45.18 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s804-nr-100000-n5.txt
Download as CSV file: xf-s804-nr-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S804 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4794   0.06794   0.06228  -0.0746   1.0000   0.0365
 -11.000  -0.5113   0.06249   0.05672  -0.0770   1.0000   0.0365
 -10.750  -0.5374   0.05860   0.05276  -0.0774   1.0000   0.0364
 -10.500  -0.5639   0.05572   0.04984  -0.0763   1.0000   0.0363
 -10.250  -0.5802   0.05053   0.04428  -0.0824   0.9872   0.0366
 -10.000  -0.5582   0.04754   0.04122  -0.0872   0.9734   0.0373
  -9.750  -0.5388   0.04456   0.03806  -0.0911   0.9565   0.0379
  -9.500  -0.5219   0.04163   0.03489  -0.0939   0.9381   0.0386
  -9.250  -0.4999   0.03875   0.03169  -0.0967   0.9229   0.0395
  -9.000  -0.4724   0.03599   0.02855  -0.0996   0.9097   0.0405
  -8.750  -0.4399   0.03387   0.02619  -0.1026   0.8964   0.0421
  -8.500  -0.4066   0.03238   0.02462  -0.1049   0.8804   0.0438
  -8.250  -0.3728   0.03066   0.02261  -0.1072   0.8638   0.0458
  -8.000  -0.3362   0.02912   0.02091  -0.1095   0.8475   0.0474
  -7.750  -0.2996   0.02789   0.01958  -0.1118   0.8305   0.0493
  -7.500  -0.2659   0.02678   0.01821  -0.1134   0.8124   0.0522
  -7.250  -0.2361   0.02588   0.01729  -0.1144   0.7934   0.0545
  -7.000  -0.2080   0.02506   0.01632  -0.1148   0.7750   0.0573
  -6.750  -0.1811   0.02428   0.01545  -0.1150   0.7578   0.0600
  -6.250  -0.1300   0.02296   0.01395  -0.1152   0.7248   0.0680
  -6.000  -0.1047   0.02236   0.01323  -0.1152   0.7097   0.0732
  -5.750  -0.0790   0.02173   0.01255  -0.1154   0.6958   0.0803
  -5.500  -0.0534   0.02111   0.01188  -0.1156   0.6819   0.0904
  -5.250  -0.0277   0.02045   0.01124  -0.1159   0.6686   0.1050
  -5.000  -0.0006   0.01981   0.01061  -0.1165   0.6568   0.1297
  -4.750   0.0261   0.01913   0.01005  -0.1172   0.6441   0.1672
  -4.500   0.0539   0.01847   0.00953  -0.1181   0.6330   0.2197
  -4.250   0.0817   0.01787   0.00921  -0.1189   0.6216   0.2916
  -4.000   0.1092   0.01773   0.00936  -0.1190   0.6114   0.3722
  -3.750   0.1370   0.01791   0.00954  -0.1187   0.6012   0.4219
  -3.500   0.1658   0.01809   0.00955  -0.1187   0.5917   0.4526
  -3.250   0.1935   0.01830   0.00964  -0.1184   0.5819   0.4736
  -3.000   0.2216   0.01852   0.00967  -0.1181   0.5733   0.4920
  -2.750   0.2476   0.01876   0.00988  -0.1173   0.5641   0.5053
  -2.500   0.2753   0.01895   0.00990  -0.1170   0.5566   0.5185
  -2.250   0.3027   0.01912   0.00997  -0.1167   0.5486   0.5309
  -2.000   0.3293   0.01928   0.01005  -0.1161   0.5413   0.5406
  -1.750   0.3572   0.01944   0.01004  -0.1159   0.5351   0.5509
  -1.500   0.3843   0.01954   0.01009  -0.1157   0.5276   0.5597
  -1.250   0.4109   0.01968   0.01015  -0.1151   0.5209   0.5673
  -1.000   0.4406   0.01977   0.01002  -0.1156   0.5151   0.5766
  -0.750   0.4664   0.01988   0.01015  -0.1150   0.5084   0.5820
  -0.500   0.4934   0.01999   0.01019  -0.1147   0.5024   0.5882
  -0.250   0.5226   0.02009   0.01012  -0.1151   0.4976   0.5953
   0.000   0.5505   0.02020   0.01017  -0.1151   0.4925   0.6008
   0.250   0.5771   0.02033   0.01029  -0.1148   0.4872   0.6055
   0.500   0.6049   0.02046   0.01035  -0.1148   0.4825   0.6110
   0.750   0.6343   0.02059   0.01033  -0.1153   0.4783   0.6172
   1.000   0.6618   0.02074   0.01045  -0.1152   0.4740   0.6218
   1.250   0.6878   0.02090   0.01063  -0.1149   0.4690   0.6262
   1.500   0.7151   0.02107   0.01077  -0.1149   0.4645   0.6318
   1.750   0.7439   0.02124   0.01084  -0.1152   0.4607   0.6381
   2.000   0.7721   0.02144   0.01095  -0.1153   0.4577   0.6428
   2.250   0.7978   0.02167   0.01125  -0.1150   0.4539   0.6475
   2.500   0.8245   0.02193   0.01153  -0.1149   0.4501   0.6535
   2.750   0.8526   0.02219   0.01176  -0.1152   0.4466   0.6604
   3.000   0.8787   0.02241   0.01200  -0.1148   0.4434   0.6655
   3.250   0.9061   0.02265   0.01220  -0.1148   0.4405   0.6715
   3.500   0.9344   0.02293   0.01244  -0.1151   0.4377   0.6782
   3.750   0.9586   0.02327   0.01288  -0.1146   0.4341   0.6843
   4.000   0.9834   0.02360   0.01330  -0.1142   0.4308   0.6912
   4.250   1.0100   0.02396   0.01368  -0.1142   0.4279   0.6995
   4.500   1.0355   0.02428   0.01404  -0.1139   0.4253   0.7063
   4.750   1.0622   0.02461   0.01437  -0.1138   0.4230   0.7143
   5.000   1.0900   0.02494   0.01469  -0.1140   0.4208   0.7225
   5.250   1.1143   0.02535   0.01517  -0.1135   0.4183   0.7310
   5.500   1.1363   0.02585   0.01582  -0.1129   0.4151   0.7411
   5.750   1.1578   0.02631   0.01642  -0.1120   0.4121   0.7508
   6.000   1.1811   0.02678   0.01698  -0.1115   0.4095   0.7620
   6.250   1.2045   0.02722   0.01749  -0.1109   0.4072   0.7736
   6.500   1.2287   0.02761   0.01795  -0.1104   0.4051   0.7858
   6.750   1.2539   0.02797   0.01834  -0.1101   0.4030   0.8001
   7.000   1.2794   0.02832   0.01871  -0.1098   0.4010   0.8161
   7.250   1.2917   0.02903   0.01968  -0.1076   0.3981   0.8344
   7.500   1.3050   0.02968   0.02055  -0.1055   0.3954   0.8587
   7.750   1.3202   0.03026   0.02130  -0.1038   0.3926   0.8951
   8.000   1.3378   0.03068   0.02185  -0.1024   0.3899   1.0000
   8.250   1.3639   0.03127   0.02246  -0.1027   0.3874   1.0000
   8.500   1.3923   0.03176   0.02292  -0.1033   0.3852   1.0000
   8.750   1.4236   0.03218   0.02329  -0.1041   0.3832   1.0000
   9.000   1.4288   0.03353   0.02489  -0.1018   0.3796   1.0000
   9.250   1.4362   0.03478   0.02631  -0.0997   0.3761   1.0000
   9.500   1.4490   0.03573   0.02736  -0.0982   0.3728   1.0000
   9.750   1.4684   0.03635   0.02803  -0.0974   0.3698   1.0000
  10.000   1.4973   0.03660   0.02826  -0.0977   0.3672   1.0000
  10.250   1.5242   0.03698   0.02864  -0.0978   0.3645   1.0000
  10.500   1.4927   0.03949   0.03145  -0.0913   0.3601   1.0000
  10.750   1.4793   0.04156   0.03368  -0.0875   0.3559   1.0000
  11.000   1.4910   0.04243   0.03461  -0.0862   0.3524   1.0000
  11.250   1.5286   0.04191   0.03406  -0.0869   0.3495   1.0000
  11.500   1.5279   0.04354   0.03580  -0.0847   0.3459   1.0000
  11.750   1.2773   0.06992   0.06274  -0.0805   0.3273   1.0000
  12.000   1.3351   0.06551   0.05833  -0.0791   0.3282   1.0000
  12.250   1.4086   0.05969   0.05249  -0.0779   0.3289   1.0000
  12.500   1.3094   0.07487   0.06785  -0.0803   0.3148   1.0000
  12.750   1.3525   0.07208   0.06509  -0.0791   0.3141   1.0000
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