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 S809 Airfoil (s809-nr) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NREL's S809 Airfoil (s809-nr)
Reynolds number: 200,000
Max Cl/Cd: 53.87 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s809-nr-200000-n5.txt
Download as CSV file: xf-s809-nr-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S809 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
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.6557   0.11087   0.10674  -0.0467   1.0000   0.0085
 -16.000  -0.6733   0.10435   0.10007  -0.0493   1.0000   0.0081
 -15.750  -0.6944   0.09770   0.09323  -0.0515   1.0000   0.0084
 -15.500  -0.7112   0.09201   0.08736  -0.0532   1.0000   0.0083
 -15.250  -0.7272   0.08659   0.08175  -0.0543   1.0000   0.0081
 -15.000  -0.7389   0.08206   0.07704  -0.0551   1.0000   0.0081
 -14.750  -0.7509   0.07754   0.07231  -0.0556   1.0000   0.0082
 -14.500  -0.7582   0.07358   0.06816  -0.0557   1.0000   0.0081
 -14.250  -0.7624   0.07006   0.06444  -0.0557   1.0000   0.0080
 -14.000  -0.7644   0.06657   0.06073  -0.0553   1.0000   0.0080
 -13.750  -0.7641   0.06391   0.05789  -0.0551   1.0000   0.0085
 -13.500  -0.7258   0.05935   0.05273  -0.0631   0.8505   0.0090
 -13.250  -0.7064   0.05715   0.04983  -0.0633   0.7647   0.0092
 -13.000  -0.6913   0.05550   0.04775  -0.0627   0.7393   0.0095
 -12.500  -0.6434   0.05376   0.04556  -0.0615   0.7118   0.0096
 -12.250  -0.6185   0.05338   0.04504  -0.0607   0.7030   0.0097
 -12.000  -0.5953   0.05308   0.04466  -0.0599   0.6955   0.0100
 -11.750  -0.5740   0.05275   0.04422  -0.0592   0.6896   0.0100
 -11.500  -0.5541   0.05233   0.04375  -0.0585   0.6843   0.0103
 -11.250  -0.5354   0.05189   0.04324  -0.0577   0.6798   0.0104
 -11.000  -0.5191   0.05128   0.04256  -0.0570   0.6762   0.0110
 -10.750  -0.5040   0.05050   0.04172  -0.0564   0.6730   0.0110
 -10.500  -0.4908   0.04954   0.04072  -0.0558   0.6699   0.0115
 -10.250  -0.4795   0.04844   0.03956  -0.0552   0.6671   0.0119
 -10.000  -0.4685   0.04725   0.03830  -0.0547   0.6645   0.0121
  -9.750  -0.4621   0.04572   0.03673  -0.0540   0.6623   0.0132
  -9.500  -0.4538   0.04432   0.03526  -0.0535   0.6603   0.0137
  -9.250  -0.4453   0.04294   0.03381  -0.0530   0.6584   0.0141
  -9.000  -0.4351   0.04167   0.03249  -0.0525   0.6564   0.0152
  -8.750  -0.4280   0.04021   0.03097  -0.0519   0.6545   0.0167
  -8.500  -0.4194   0.03891   0.02964  -0.0513   0.6527   0.0196
  -8.250  -0.4132   0.03746   0.02816  -0.0505   0.6509   0.0227
  -8.000  -0.4079   0.03601   0.02668  -0.0496   0.6494   0.0286
  -7.750  -0.4041   0.03454   0.02521  -0.0486   0.6479   0.0386
  -7.500  -0.4119   0.03246   0.02331  -0.0468   0.6466   0.0738
  -7.250  -0.4374   0.02934   0.02053  -0.0439   0.6454   0.1459
  -7.000  -0.4654   0.02607   0.01750  -0.0406   0.6442   0.2061
  -6.750  -0.4886   0.02308   0.01464  -0.0376   0.6430   0.2426
  -6.500  -0.5169   0.02025   0.01189  -0.0337   0.6416   0.2713
  -6.250  -0.5447   0.01725   0.00926  -0.0303   0.6400   0.3567
  -5.750  -0.4896   0.01980   0.01233  -0.0295   0.6368   0.4947
  -5.500  -0.4366   0.02352   0.01612  -0.0299   0.6355   0.5073
  -5.250  -0.4106   0.02345   0.01594  -0.0300   0.6343   0.5090
  -5.000  -0.3903   0.02278   0.01514  -0.0300   0.6332   0.5114
  -4.750  -0.3757   0.02150   0.01365  -0.0301   0.6321   0.5154
  -4.500  -0.3560   0.02059   0.01252  -0.0304   0.6311   0.5181
  -4.250  -0.3285   0.02044   0.01229  -0.0307   0.6302   0.5188
  -4.000  -0.3011   0.02030   0.01208  -0.0311   0.6293   0.5195
  -3.750  -0.2736   0.02020   0.01190  -0.0315   0.6285   0.5204
  -3.500  -0.2460   0.02011   0.01174  -0.0319   0.6277   0.5214
  -3.250  -0.2187   0.01999   0.01159  -0.0323   0.6268   0.5225
  -3.000  -0.1917   0.01983   0.01138  -0.0328   0.6260   0.5237
  -2.750  -0.1649   0.01963   0.01114  -0.0332   0.6251   0.5250
  -2.500  -0.1381   0.01941   0.01087  -0.0337   0.6242   0.5265
  -2.250  -0.1114   0.01917   0.01056  -0.0343   0.6233   0.5281
  -2.000  -0.0847   0.01890   0.01022  -0.0349   0.6222   0.5299
  -1.750  -0.0579   0.01861   0.00984  -0.0356   0.6211   0.5317
  -1.500  -0.0304   0.01844   0.00961  -0.0362   0.6200   0.5331
  -1.250  -0.0022   0.01843   0.00962  -0.0366   0.6192   0.5339
  -1.000   0.0259   0.01843   0.00964  -0.0371   0.6183   0.5348
  -0.750   0.0541   0.01843   0.00965  -0.0376   0.6176   0.5358
  -0.500   0.0822   0.01843   0.00966  -0.0380   0.6168   0.5367
  -0.250   0.1104   0.01841   0.00965  -0.0386   0.6161   0.5377
   0.000   0.1385   0.01840   0.00965  -0.0391   0.6154   0.5388
   0.250   0.1667   0.01839   0.00964  -0.0397   0.6147   0.5400
   0.500   0.1950   0.01837   0.00962  -0.0402   0.6138   0.5412
   0.750   0.2235   0.01835   0.00960  -0.0409   0.6129   0.5426
   1.000   0.2520   0.01836   0.00960  -0.0415   0.6122   0.5442
   1.250   0.2800   0.01837   0.00962  -0.0422   0.6115   0.5459
   1.500   0.3076   0.01838   0.00965  -0.0428   0.6105   0.5476
   1.750   0.3348   0.01842   0.00977  -0.0432   0.6091   0.5486
   2.000   0.3619   0.01849   0.00994  -0.0435   0.6076   0.5494
   2.250   0.3892   0.01857   0.01012  -0.0438   0.6059   0.5503
   2.500   0.4165   0.01865   0.01029  -0.0441   0.6044   0.5512
   2.750   0.4441   0.01874   0.01046  -0.0445   0.6029   0.5522
   3.000   0.4719   0.01883   0.01063  -0.0449   0.6015   0.5533
   3.250   0.4999   0.01892   0.01079  -0.0453   0.6000   0.5546
   3.500   0.5282   0.01900   0.01093  -0.0458   0.5987   0.5560
   3.750   0.5570   0.01907   0.01106  -0.0464   0.5973   0.5575
   4.000   0.5849   0.01916   0.01122  -0.0468   0.5954   0.5590
   4.250   0.6093   0.01928   0.01148  -0.0467   0.5918   0.5604
   4.500   0.6358   0.01932   0.01161  -0.0469   0.5881   0.5618
   4.750   0.6647   0.01922   0.01155  -0.0474   0.5845   0.5631
   5.000   0.6960   0.01899   0.01133  -0.0480   0.5808   0.5641
   5.250   0.7184   0.01897   0.01153  -0.0474   0.5738   0.5651
   5.500   0.7473   0.01862   0.01125  -0.0475   0.5672   0.5662
   5.750   0.7723   0.01843   0.01119  -0.0471   0.5592   0.5674
   6.000   0.7999   0.01805   0.01089  -0.0469   0.5507   0.5688
   6.250   0.8226   0.01793   0.01097  -0.0462   0.5410   0.5702
   6.500   0.8479   0.01770   0.01086  -0.0458   0.5312   0.5717
   6.750   0.8706   0.01756   0.01089  -0.0451   0.5165   0.5732
   7.000   0.8920   0.01742   0.01092  -0.0442   0.4903   0.5746
   7.250   0.9094   0.01688   0.00997  -0.0419   0.4208   0.5760
   7.500   0.9075   0.01767   0.01031  -0.0372   0.3526   0.5772
   7.750   0.9012   0.01872   0.01106  -0.0323   0.3010   0.5784
   8.000   0.8917   0.01975   0.01191  -0.0269   0.2621   0.5794
   8.250   0.8850   0.02105   0.01307  -0.0227   0.2269   0.5803
   8.500   0.8790   0.02253   0.01443  -0.0192   0.1954   0.5813
   8.750   0.8747   0.02416   0.01598  -0.0164   0.1677   0.5824
   9.000   0.8727   0.02589   0.01763  -0.0144   0.1437   0.5836
   9.250   0.8727   0.02767   0.01934  -0.0128   0.1221   0.5850
   9.500   0.8753   0.02938   0.02098  -0.0116   0.1038   0.5865
   9.750   0.8795   0.03102   0.02258  -0.0105   0.0879   0.5880
  10.000   0.8849   0.03262   0.02415  -0.0096   0.0753   0.5895
  10.250   0.8910   0.03420   0.02571  -0.0088   0.0649   0.5910
  10.500   0.8972   0.03580   0.02728  -0.0081   0.0567   0.5924
  10.750   0.9059   0.03726   0.02877  -0.0075   0.0500   0.5938
  11.000   0.9127   0.03885   0.03040  -0.0068   0.0447   0.5951
  11.250   0.9210   0.04035   0.03197  -0.0063   0.0402   0.5963
  11.500   0.9267   0.04209   0.03374  -0.0057   0.0371   0.5975
  11.750   0.9356   0.04361   0.03538  -0.0052   0.0342   0.5990
  12.000   0.9431   0.04530   0.03713  -0.0048   0.0315   0.6005
  12.250   0.9484   0.04721   0.03907  -0.0044   0.0294   0.6020
  12.500   0.9571   0.04889   0.04088  -0.0041   0.0277   0.6038
  12.750   0.9651   0.05067   0.04276  -0.0040   0.0260   0.6056
  13.000   0.9716   0.05264   0.04480  -0.0038   0.0247   0.6075
  13.250   0.9752   0.05495   0.04712  -0.0037   0.0235   0.6094
  13.500   0.9832   0.05684   0.04916  -0.0036   0.0225   0.6111
  13.750   0.9910   0.05879   0.05125  -0.0036   0.0213   0.6129
  14.000   0.9980   0.06086   0.05344  -0.0037   0.0202   0.6148
  14.250   1.0040   0.06312   0.05579  -0.0038   0.0195   0.6167
  14.500   1.0084   0.06560   0.05832  -0.0041   0.0187   0.6187
  14.750   1.0138   0.06800   0.06083  -0.0043   0.0181   0.6207
  15.000   1.0204   0.07035   0.06335  -0.0046   0.0175   0.6229
  15.250   1.0262   0.07287   0.06600  -0.0050   0.0167   0.6251
  15.500   1.0313   0.07547   0.06876  -0.0055   0.0161   0.6269
  15.750   1.0353   0.07828   0.07169  -0.0062   0.0155   0.6290
  16.000   1.0386   0.08123   0.07476  -0.0070   0.0151   0.6312
  16.250   1.0404   0.08442   0.07803  -0.0081   0.0145   0.6336
  16.500   1.0417   0.08780   0.08154  -0.0091   0.0141   0.6360
  16.750   1.0430   0.09130   0.08525  -0.0102   0.0137   0.6386
  17.000   1.0427   0.09511   0.08925  -0.0115   0.0133   0.6410
  17.250   1.0412   0.09919   0.09353  -0.0132   0.0128   0.6433
  17.500   1.0389   0.10345   0.09798  -0.0150   0.0125   0.6459
  17.750   1.0358   0.10798   0.10268  -0.0173   0.0121   0.6487
  18.000   1.0324   0.11265   0.10749  -0.0197   0.0118   0.6518
  18.250   1.0284   0.11749   0.11249  -0.0223   0.0116   0.6548
  18.500   1.0246   0.12241   0.11752  -0.0251   0.0113   0.6577
  18.750   1.0196   0.12758   0.12283  -0.0281   0.0111   0.6605
  19.000   1.0120   0.13341   0.12881  -0.0316   0.0108   0.6634
<< Back to NREL's S809 Airfoil (s809-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S809 Airfoil (s809-nr)