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NREL's S808 Airfoil (s808-nr) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NREL's S808 Airfoil (s808-nr)
Reynolds number: 100,000
Max Cl/Cd: 41.38 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s808-nr-100000-n5.txt
Download as CSV file: xf-s808-nr-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S808 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.4784   0.10336   0.09618  -0.0387   1.0000   0.2132
 -12.000  -0.4650   0.10253   0.09535  -0.0379   1.0000   0.2155
 -11.750  -0.5017   0.09520   0.08798  -0.0405   1.0000   0.2254
 -11.500  -0.4823   0.09518   0.08796  -0.0393   1.0000   0.2265
 -11.250  -0.4656   0.09480   0.08759  -0.0382   1.0000   0.2279
 -11.000  -0.4530   0.09393   0.08672  -0.0373   1.0000   0.2300
 -10.500  -0.4829   0.08557   0.07833  -0.0385   1.0000   0.2414
  -8.500  -0.7634   0.04027   0.03282  -0.0455   0.9845   0.2897
  -8.250  -0.7221   0.04028   0.03283  -0.0475   0.9797   0.2909
  -8.000  -0.6870   0.03999   0.03253  -0.0491   0.9728   0.2923
  -7.750  -0.6501   0.03947   0.03198  -0.0515   0.9662   0.2943
  -7.500  -0.6279   0.03752   0.02992  -0.0543   0.9552   0.2979
  -7.250  -0.6234   0.03233   0.02420  -0.0603   0.9399   0.3050
  -7.000  -0.5871   0.03135   0.02315  -0.0630   0.9334   0.3072
  -6.750  -0.5596   0.03098   0.02281  -0.0630   0.9217   0.3087
  -6.500  -0.5266   0.03051   0.02235  -0.0642   0.9126   0.3106
  -6.250  -0.4944   0.02993   0.02173  -0.0655   0.9028   0.3130
  -6.000  -0.4659   0.02908   0.02080  -0.0666   0.8913   0.3161
  -5.750  -0.4316   0.02772   0.01925  -0.0694   0.8832   0.3202
  -5.500  -0.4041   0.02637   0.01766  -0.0711   0.8704   0.3239
  -5.250  -0.3633   0.02598   0.01732  -0.0731   0.8634   0.3257
  -5.000  -0.3314   0.02562   0.01697  -0.0737   0.8505   0.3277
  -4.750  -0.2925   0.02518   0.01651  -0.0758   0.8403   0.3303
  -4.500  -0.2548   0.02463   0.01589  -0.0778   0.8286   0.3336
  -4.250  -0.2192   0.02394   0.01505  -0.0798   0.8151   0.3377
  -4.000  -0.1800   0.02311   0.01398  -0.0826   0.8027   0.3420
  -3.750  -0.1440   0.02286   0.01376  -0.0838   0.7883   0.3441
  -3.500  -0.1105   0.02263   0.01352  -0.0847   0.7727   0.3465
  -3.250  -0.0769   0.02237   0.01319  -0.0857   0.7576   0.3493
  -3.000  -0.0431   0.02206   0.01277  -0.0869   0.7427   0.3528
  -2.750  -0.0119   0.02169   0.01224  -0.0878   0.7271   0.3570
  -2.500   0.0180   0.02137   0.01179  -0.0884   0.7117   0.3608
  -2.250   0.0476   0.02131   0.01173  -0.0885   0.6970   0.3634
  -2.000   0.0779   0.02123   0.01160  -0.0888   0.6834   0.3664
  -1.750   0.1053   0.02111   0.01144  -0.0887   0.6686   0.3697
  -1.500   0.1338   0.02094   0.01117  -0.0889   0.6549   0.3735
  -1.250   0.1638   0.02073   0.01076  -0.0895   0.6424   0.3779
  -1.000   0.1904   0.02066   0.01072  -0.0892   0.6286   0.3809
  -0.750   0.2178   0.02067   0.01073  -0.0889   0.6162   0.3841
  -0.500   0.2456   0.02066   0.01068  -0.0888   0.6041   0.3879
  -0.250   0.2728   0.02061   0.01058  -0.0887   0.5917   0.3922
   0.000   0.3018   0.02051   0.01032  -0.0890   0.5806   0.3969
   0.250   0.3282   0.02049   0.01033  -0.0887   0.5685   0.4001
   0.500   0.3553   0.02054   0.01038  -0.0884   0.5579   0.4036
   0.750   0.3820   0.02057   0.01042  -0.0881   0.5465   0.4078
   1.000   0.4096   0.02059   0.01038  -0.0880   0.5361   0.4129
   1.250   0.4373   0.02059   0.01029  -0.0880   0.5254   0.4179
   1.500   0.4635   0.02066   0.01042  -0.0876   0.5152   0.4214
   1.750   0.4899   0.02074   0.01051  -0.0872   0.5051   0.4255
   2.000   0.5168   0.02082   0.01057  -0.0870   0.4953   0.4306
   2.250   0.5443   0.02088   0.01055  -0.0870   0.4854   0.4366
   2.500   0.5702   0.02099   0.01072  -0.0865   0.4761   0.4407
   2.750   0.5961   0.02111   0.01088  -0.0860   0.4666   0.4455
   3.000   0.6227   0.02124   0.01099  -0.0858   0.4577   0.4511
   3.500   0.6751   0.02151   0.01126  -0.0851   0.4400   0.4616
   3.750   0.7001   0.02168   0.01151  -0.0845   0.4306   0.4672
   4.000   0.7269   0.02186   0.01161  -0.0843   0.4228   0.4740
   4.250   0.7518   0.02203   0.01188  -0.0838   0.4136   0.4798
   4.500   0.7768   0.02223   0.01210  -0.0832   0.4057   0.4852
   4.750   0.8019   0.02245   0.01237  -0.0827   0.3974   0.4919
   5.000   0.8269   0.02267   0.01260  -0.0822   0.3892   0.4989
   5.250   0.8511   0.02292   0.01288  -0.0815   0.3821   0.5050
   5.500   0.8748   0.02318   0.01323  -0.0808   0.3735   0.5125
   5.750   0.8997   0.02344   0.01345  -0.0802   0.3665   0.5200
   6.000   0.9224   0.02373   0.01387  -0.0793   0.3588   0.5264
   6.250   0.9458   0.02402   0.01420  -0.0786   0.3512   0.5346
   6.500   0.9695   0.02434   0.01452  -0.0779   0.3445   0.5423
   6.750   0.9912   0.02468   0.01501  -0.0769   0.3369   0.5503
   7.000   1.0145   0.02502   0.01532  -0.0762   0.3302   0.5598
   7.250   1.0355   0.02540   0.01581  -0.0751   0.3233   0.5672
   7.500   1.0566   0.02578   0.01628  -0.0741   0.3162   0.5768
   7.750   1.0782   0.02616   0.01664  -0.0731   0.3102   0.5855
   8.000   1.0975   0.02661   0.01723  -0.0718   0.3032   0.5954
   8.250   1.1166   0.02704   0.01774  -0.0706   0.2966   0.6050
   8.500   1.1371   0.02748   0.01816  -0.0695   0.2911   0.6156
   8.750   1.1527   0.02799   0.01885  -0.0677   0.2844   0.6257
   9.000   1.1686   0.02846   0.01939  -0.0660   0.2784   0.6370
   9.250   1.1860   0.02895   0.01988  -0.0644   0.2732   0.6481
   9.500   1.1995   0.02960   0.02069  -0.0626   0.2669   0.6607
   9.750   1.2132   0.03019   0.02138  -0.0606   0.2612   0.6725
  10.000   1.2297   0.03077   0.02193  -0.0592   0.2564   0.6861
  10.500   1.2515   0.03230   0.02379  -0.0551   0.2450   0.7152
  10.750   1.2646   0.03297   0.02449  -0.0534   0.2404   0.7320
  11.000   1.2730   0.03389   0.02559  -0.0513   0.2352   0.7503
  11.250   1.2803   0.03482   0.02669  -0.0491   0.2300   0.7712
  11.750   1.2939   0.03650   0.02856  -0.0445   0.2214   0.8320
  12.000   1.2860   0.03734   0.02970  -0.0404   0.2173   0.9689
  12.250   1.2951   0.03878   0.03119  -0.0397   0.2122   1.0000
  12.500   1.3064   0.04007   0.03243  -0.0391   0.2080   1.0000
  12.750   1.3124   0.04184   0.03427  -0.0384   0.2036   1.0000
  13.000   1.3155   0.04384   0.03639  -0.0378   0.1988   1.0000
  13.250   1.3208   0.04569   0.03826  -0.0373   0.1945   1.0000
  13.500   1.3313   0.04720   0.03969  -0.0369   0.1908   1.0000
  13.750   1.3273   0.05008   0.04277  -0.0367   0.1865   1.0000
  14.000   1.3266   0.05274   0.04554  -0.0366   0.1823   1.0000
  14.250   1.3303   0.05501   0.04783  -0.0366   0.1785   1.0000
  14.500   1.3355   0.05724   0.05004  -0.0367   0.1750   1.0000
  14.750   1.3255   0.06127   0.05429  -0.0374   0.1711   1.0000
  15.000   1.3205   0.06483   0.05796  -0.0381   0.1673   1.0000
  15.250   1.3231   0.06754   0.06068  -0.0386   0.1638   1.0000
  15.500   1.3249   0.07046   0.06362  -0.0393   0.1605   1.0000
  15.750   1.3046   0.07649   0.06989  -0.0414   0.1569   1.0000
  16.000   1.2930   0.08153   0.07508  -0.0433   0.1532   1.0000
  16.250   1.2962   0.08448   0.07803  -0.0443   0.1500   1.0000
  16.500   1.2979   0.08771   0.08128  -0.0453   0.1470   1.0000
  16.750   1.2485   0.09926   0.09319  -0.0511   0.1430   1.0000
  17.000   1.2239   0.10721   0.10130  -0.0551   0.1391   1.0000
  17.250   1.2434   0.10766   0.10168  -0.0549   0.1365   1.0000
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