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NREL's S811 Airfoil (s811-nr) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NREL's S811 Airfoil (s811-nr)
Reynolds number: 100,000
Max Cl/Cd: 28.39 at α=10.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s811-nr-100000-n5.txt
Download as CSV file: xf-s811-nr-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S811 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1936   0.11612   0.10832  -0.0183   1.0000   0.3027
  -9.000  -0.1940   0.11415   0.10637  -0.0182   1.0000   0.3052
  -8.750  -0.1869   0.11088   0.10309  -0.0209   0.9918   0.3075
  -8.500  -0.1509   0.10840   0.10062  -0.0246   0.9704   0.3083
  -8.250  -0.1179   0.10588   0.09809  -0.0284   0.8987   0.3093
  -8.000  -0.0108   0.09976   0.09128  -0.0498   0.7714   0.3115
  -7.750   0.0144   0.09820   0.08930  -0.0521   0.7070   0.3136
  -7.500   0.0286   0.09678   0.08763  -0.0526   0.6712   0.3155
  -7.250   0.0402   0.09516   0.08584  -0.0531   0.6463   0.3166
  -7.000   0.0505   0.09344   0.08397  -0.0538   0.6272   0.3179
  -6.500   0.0576   0.08960   0.07991  -0.0551   0.6007   0.3218
  -6.250   0.0836   0.08859   0.07882  -0.0556   0.5866   0.3228
  -6.000   0.1059   0.08754   0.07770  -0.0559   0.5751   0.3239
  -5.750   0.1249   0.08640   0.07652  -0.0563   0.5658   0.3250
  -5.500   0.1407   0.08512   0.07518  -0.0565   0.5577   0.3260
  -5.250   0.1547   0.08376   0.07376  -0.0568   0.5513   0.3268
  -5.000   0.1682   0.08241   0.07239  -0.0569   0.5448   0.3276
  -4.750   0.1810   0.08107   0.07101  -0.0570   0.5389   0.3286
  -4.500   0.1928   0.07972   0.06959  -0.0571   0.5341   0.3295
  -4.250   0.2033   0.07840   0.06825  -0.0572   0.5294   0.3313
  -4.000   0.2071   0.07686   0.06670  -0.0572   0.5250   0.3336
  -3.750   0.2006   0.07478   0.06458  -0.0572   0.5214   0.3353
  -3.500   0.2053   0.07310   0.06288  -0.0571   0.5175   0.3364
  -3.250   0.2262   0.07219   0.06192  -0.0570   0.5133   0.3370
  -3.000   0.2456   0.07123   0.06097  -0.0569   0.5089   0.3376
  -2.750   0.2638   0.07027   0.06005  -0.0567   0.5047   0.3382
  -2.500   0.2808   0.06930   0.05910  -0.0566   0.5010   0.3389
  -2.250   0.2985   0.06845   0.05826  -0.0564   0.4977   0.3400
  -2.000   0.3155   0.06764   0.05743  -0.0561   0.4949   0.3414
  -1.750   0.3300   0.06672   0.05649  -0.0559   0.4923   0.3429
  -1.500   0.3415   0.06562   0.05544  -0.0556   0.4897   0.3442
  -1.250   0.3506   0.06436   0.05422  -0.0553   0.4871   0.3452
  -1.000   0.3583   0.06303   0.05293  -0.0549   0.4846   0.3462
  -0.750   0.3623   0.06152   0.05144  -0.0545   0.4823   0.3477
  -0.500   0.3282   0.05780   0.04769  -0.0537   0.4811   0.3514
  -0.250   0.3512   0.05744   0.04738  -0.0532   0.4783   0.3521
   0.000   0.3726   0.05701   0.04697  -0.0527   0.4758   0.3528
   0.250   0.3930   0.05656   0.04653  -0.0522   0.4735   0.3537
   0.500   0.4109   0.05604   0.04604  -0.0516   0.4711   0.3547
   0.750   0.4239   0.05528   0.04539  -0.0507   0.4688   0.3556
   1.000   0.4342   0.05442   0.04462  -0.0498   0.4666   0.3566
   1.250   0.4423   0.05356   0.04384  -0.0487   0.4646   0.3578
   1.500   0.4455   0.05263   0.04298  -0.0472   0.4627   0.3592
   1.750   0.4430   0.05151   0.04190  -0.0454   0.4610   0.3609
   2.000   0.4316   0.04931   0.03971  -0.0449   0.4595   0.3639
   2.250   0.4171   0.04583   0.03619  -0.0467   0.4583   0.3688
   2.500   0.4372   0.04560   0.03602  -0.0461   0.4564   0.3696
   2.750   0.4563   0.04516   0.03561  -0.0458   0.4547   0.3706
   3.000   0.4754   0.04456   0.03503  -0.0459   0.4529   0.3718
   3.250   0.4909   0.04379   0.03432  -0.0461   0.4509   0.3733
   3.500   0.5037   0.04256   0.03319  -0.0469   0.4486   0.3756
   3.750   0.5170   0.03683   0.02714  -0.0566   0.4467   0.3851
   4.000   0.5387   0.03698   0.02744  -0.0560   0.4446   0.3860
   4.250   0.5610   0.03708   0.02766  -0.0556   0.4426   0.3870
   4.500   0.5841   0.03706   0.02774  -0.0554   0.4404   0.3882
   4.750   0.6082   0.03696   0.02770  -0.0556   0.4383   0.3894
   5.000   0.6342   0.03675   0.02754  -0.0561   0.4362   0.3909
   5.250   0.6620   0.03648   0.02727  -0.0571   0.4344   0.3927
   5.500   0.6920   0.03612   0.02687  -0.0588   0.4329   0.3950
   5.750   0.7144   0.03586   0.02670  -0.0598   0.4302   0.3977
   6.000   0.7403   0.03539   0.02619  -0.0620   0.4271   0.4017
   6.250   0.7597   0.03577   0.02676  -0.0612   0.4241   0.4028
   6.500   0.7809   0.03610   0.02725  -0.0604   0.4213   0.4039
   6.750   0.8047   0.03634   0.02760  -0.0600   0.4187   0.4052
   7.000   0.8314   0.03647   0.02780  -0.0601   0.4163   0.4067
   7.250   0.8619   0.03648   0.02784  -0.0607   0.4141   0.4083
   7.500   0.8785   0.03696   0.02849  -0.0598   0.4107   0.4098
   7.750   0.8884   0.03765   0.02939  -0.0582   0.4062   0.4114
   8.000   0.9079   0.03794   0.02978  -0.0577   0.4022   0.4132
   8.250   0.9367   0.03782   0.02967  -0.0583   0.3988   0.4155
   8.500   0.9743   0.03736   0.02912  -0.0599   0.3957   0.4183
   8.750   0.9897   0.03780   0.02966  -0.0590   0.3911   0.4204
   9.000   0.9892   0.03873   0.03084  -0.0558   0.3852   0.4214
   9.250   1.0136   0.03853   0.03075  -0.0551   0.3804   0.4230
   9.500   1.0573   0.03751   0.02970  -0.0563   0.3762   0.4252
   9.750   1.0421   0.03891   0.03138  -0.0518   0.3699   0.4262
  10.000   1.0410   0.03947   0.03208  -0.0485   0.3641   0.4276
  10.250   1.0850   0.03822   0.03080  -0.0497   0.3588   0.4303
  10.500   1.0696   0.03960   0.03236  -0.0454   0.3529   0.4314
  10.750   1.0516   0.04158   0.03450  -0.0420   0.3462   0.4325
  11.000   1.1000   0.03974   0.03258  -0.0431   0.3403   0.4355
  11.250   0.9402   0.05382   0.04707  -0.0387   0.3278   0.4322
  11.500   1.0126   0.04884   0.04205  -0.0381   0.3247   0.4360
  11.750   0.8734   0.06665   0.06002  -0.0420   0.3015   0.4329
  12.250   0.8641   0.07338   0.06685  -0.0441   0.2791   0.4354
  12.500   0.8994   0.07172   0.06519  -0.0437   0.2745   0.4381
  12.750   0.8889   0.07598   0.06949  -0.0451   0.2614   0.4391
  13.000   0.8977   0.07761   0.07122  -0.0453   0.2516   0.4405
  13.250   0.9273   0.07638   0.07005  -0.0446   0.2430   0.4428
  13.500   0.9345   0.07826   0.07196  -0.0450   0.2298   0.4445
  13.750   0.9481   0.07927   0.07293  -0.0450   0.2159   0.4467
  14.000   0.9594   0.08062   0.07418  -0.0453   0.2009   0.4489
  14.250   0.9653   0.08282   0.07627  -0.0459   0.1861   0.4510
  14.500   0.9683   0.08556   0.07892  -0.0468   0.1724   0.4529
  14.750   0.9700   0.08859   0.08186  -0.0479   0.1598   0.4547
  15.000   0.9708   0.09184   0.08501  -0.0491   0.1481   0.4564
  15.250   0.9711   0.09531   0.08842  -0.0505   0.1373   0.4579
  15.500   0.9712   0.09881   0.09194  -0.0519   0.1274   0.4592
  15.750   0.9718   0.10227   0.09540  -0.0532   0.1186   0.4606
  16.000   0.9727   0.10571   0.09880  -0.0547   0.1104   0.4621
  16.250   0.9738   0.10931   0.10245  -0.0562   0.1025   0.4637
  16.500   0.9756   0.11278   0.10592  -0.0578   0.0957   0.4655
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