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 S808 Airfoil (s808-nr) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NREL's S808 Airfoil (s808-nr)
Reynolds number: 500,000
Max Cl/Cd: 76.57 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s808-nr-500000-n5.txt
Download as CSV file: xf-s808-nr-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.250  -0.9432   0.08787   0.08340  -0.0518   1.0000   0.0897
 -17.000  -0.9575   0.08336   0.07889  -0.0531   1.0000   0.0949
 -16.500  -0.9871   0.07449   0.07001  -0.0556   1.0000   0.1057
 -16.250  -1.0033   0.07005   0.06555  -0.0567   1.0000   0.1111
 -16.000  -1.0249   0.06513   0.06062  -0.0579   1.0000   0.1171
 -15.750  -1.0457   0.06045   0.05592  -0.0589   1.0000   0.1229
 -15.500  -1.0704   0.05554   0.05100  -0.0599   1.0000   0.1299
 -15.250  -1.0943   0.05091   0.04635  -0.0606   1.0000   0.1355
 -15.000  -1.1189   0.04646   0.04188  -0.0609   1.0000   0.1424
 -14.750  -1.1450   0.04225   0.03764  -0.0609   1.0000   0.1480
 -14.500  -1.1683   0.03854   0.03390  -0.0604   1.0000   0.1539
 -14.250  -1.1935   0.03489   0.03023  -0.0595   1.0000   0.1592
 -14.000  -1.2150   0.03179   0.02710  -0.0581   1.0000   0.1644
 -13.750  -1.2317   0.02926   0.02452  -0.0564   1.0000   0.1689
 -13.500  -1.2438   0.02629   0.02152  -0.0565   0.9988   0.1742
 -13.250  -1.2237   0.02427   0.01944  -0.0602   0.9951   0.1816
 -13.000  -1.2061   0.02212   0.01726  -0.0641   0.9911   0.1879
 -12.750  -1.1888   0.02058   0.01565  -0.0661   0.9865   0.1937
 -12.500  -1.1605   0.01931   0.01432  -0.0694   0.9830   0.1986
 -12.250  -1.1283   0.01835   0.01334  -0.0726   0.9806   0.2050
 -12.000  -1.0932   0.01784   0.01274  -0.0751   0.9791   0.2102
 -11.750  -1.0703   0.01717   0.01207  -0.0756   0.9752   0.2144
 -11.500  -1.0431   0.01666   0.01154  -0.0765   0.9715   0.2187
 -11.250  -1.0108   0.01629   0.01110  -0.0781   0.9690   0.2234
 -11.000  -0.9769   0.01586   0.01066  -0.0800   0.9669   0.2287
 -10.500  -0.9096   0.01519   0.00995  -0.0833   0.9628   0.2363
 -10.250  -0.8869   0.01488   0.00958  -0.0827   0.9570   0.2382
 -10.000  -0.8540   0.01458   0.00922  -0.0839   0.9539   0.2397
  -9.750  -0.8188   0.01424   0.00884  -0.0856   0.9515   0.2414
  -9.500  -0.7820   0.01388   0.00848  -0.0877   0.9497   0.2436
  -9.250  -0.7635   0.01359   0.00818  -0.0861   0.9410   0.2453
  -9.000  -0.7311   0.01329   0.00786  -0.0871   0.9365   0.2471
  -8.750  -0.6953   0.01299   0.00753  -0.0888   0.9333   0.2490
  -8.500  -0.6774   0.01274   0.00725  -0.0869   0.9206   0.2506
  -8.250  -0.6465   0.01248   0.00695  -0.0875   0.9128   0.2523
  -8.000  -0.6119   0.01222   0.00664  -0.0889   0.9031   0.2541
  -7.750  -0.5712   0.01198   0.00634  -0.0913   0.8933   0.2558
  -7.500  -0.5264   0.01166   0.00598  -0.0947   0.8807   0.2583
  -7.250  -0.4835   0.01139   0.00565  -0.0977   0.8609   0.2605
  -7.000  -0.4478   0.01124   0.00538  -0.0992   0.8349   0.2625
  -6.750  -0.4174   0.01116   0.00517  -0.0996   0.8087   0.2645
  -6.500  -0.3894   0.01112   0.00500  -0.0995   0.7850   0.2665
  -6.250  -0.3621   0.01108   0.00484  -0.0994   0.7628   0.2684
  -6.000  -0.3349   0.01106   0.00469  -0.0992   0.7424   0.2702
  -5.750  -0.3077   0.01104   0.00456  -0.0990   0.7233   0.2718
  -5.500  -0.2806   0.01098   0.00442  -0.0988   0.7051   0.2740
  -5.250  -0.2532   0.01091   0.00431  -0.0987   0.6884   0.2765
  -5.000  -0.2256   0.01087   0.00420  -0.0986   0.6724   0.2788
  -4.750  -0.1979   0.01084   0.00410  -0.0985   0.6575   0.2811
  -4.500  -0.1703   0.01083   0.00401  -0.0983   0.6425   0.2833
  -4.250  -0.1421   0.01080   0.00391  -0.0983   0.6283   0.2855
  -4.000  -0.1140   0.01079   0.00383  -0.0983   0.6152   0.2874
  -3.750  -0.0861   0.01080   0.00375  -0.0982   0.6018   0.2891
  -3.500  -0.0577   0.01074   0.00367  -0.0982   0.5888   0.2916
  -3.250  -0.0294   0.01072   0.00361  -0.0982   0.5770   0.2941
  -3.000  -0.0012   0.01071   0.00355  -0.0982   0.5645   0.2968
  -2.750   0.0274   0.01070   0.00351  -0.0982   0.5532   0.2996
  -2.250   0.0844   0.01073   0.00342  -0.0982   0.5307   0.3045
  -2.000   0.1126   0.01076   0.00339  -0.0981   0.5198   0.3065
  -1.750   0.1415   0.01073   0.00336  -0.0982   0.5096   0.3093
  -1.500   0.1698   0.01075   0.00334  -0.0982   0.4993   0.3119
  -1.250   0.1985   0.01076   0.00333  -0.0983   0.4887   0.3147
  -1.000   0.2269   0.01080   0.00333  -0.0982   0.4795   0.3174
  -0.750   0.2557   0.01083   0.00332  -0.0983   0.4696   0.3202
  -0.500   0.2839   0.01090   0.00333  -0.0982   0.4599   0.3229
  -0.250   0.3127   0.01091   0.00334  -0.0982   0.4507   0.3259
   0.000   0.3408   0.01096   0.00337  -0.0982   0.4418   0.3291
   0.250   0.3697   0.01099   0.00339  -0.0982   0.4327   0.3321
   0.500   0.3977   0.01106   0.00343  -0.0981   0.4236   0.3352
   0.750   0.4264   0.01111   0.00346  -0.0981   0.4155   0.3382
   1.000   0.4544   0.01120   0.00351  -0.0980   0.4063   0.3408
   1.250   0.4828   0.01125   0.00356  -0.0980   0.3985   0.3440
   1.500   0.5111   0.01131   0.00362  -0.0979   0.3901   0.3479
   1.750   0.5390   0.01140   0.00369  -0.0978   0.3821   0.3519
   2.000   0.5673   0.01148   0.00376  -0.0977   0.3740   0.3556
   2.250   0.5947   0.01160   0.00384  -0.0975   0.3662   0.3587
   2.500   0.6230   0.01167   0.00392  -0.0974   0.3589   0.3620
   2.750   0.6507   0.01177   0.00402  -0.0973   0.3508   0.3660
   3.000   0.6782   0.01188   0.00413  -0.0971   0.3438   0.3705
   3.250   0.7060   0.01198   0.00424  -0.0969   0.3363   0.3750
   3.500   0.7327   0.01215   0.00436  -0.0966   0.3286   0.3787
   3.750   0.7606   0.01223   0.00448  -0.0965   0.3222   0.3831
   4.000   0.7877   0.01236   0.00461  -0.0962   0.3150   0.3876
   4.250   0.8143   0.01252   0.00476  -0.0959   0.3080   0.3925
   4.500   0.8415   0.01265   0.00490  -0.0956   0.3014   0.3972
   4.750   0.8678   0.01281   0.00506  -0.0952   0.2944   0.4023
   5.000   0.8943   0.01296   0.00524  -0.0949   0.2882   0.4077
   5.250   0.9207   0.01312   0.00540  -0.0945   0.2815   0.4128
   5.500   0.9459   0.01334   0.00559  -0.0939   0.2749   0.4173
   5.750   0.9723   0.01348   0.00578  -0.0935   0.2689   0.4229
   6.000   0.9979   0.01367   0.00598  -0.0930   0.2626   0.4294
   6.250   1.0221   0.01391   0.00621  -0.0923   0.2563   0.4353
   6.500   1.0478   0.01407   0.00641  -0.0918   0.2507   0.4410
   6.750   1.0722   0.01429   0.00665  -0.0911   0.2444   0.4471
   7.000   1.0956   0.01455   0.00690  -0.0903   0.2385   0.4532
   7.250   1.1199   0.01475   0.00713  -0.0895   0.2330   0.4588
   7.500   1.1422   0.01499   0.00740  -0.0885   0.2271   0.4656
   7.750   1.1632   0.01526   0.00768  -0.0872   0.2217   0.4729
   8.000   1.1853   0.01548   0.00794  -0.0861   0.2165   0.4796
   8.250   1.2061   0.01577   0.00825  -0.0849   0.2109   0.4870
   8.500   1.2262   0.01611   0.00859  -0.0835   0.2056   0.4942
   8.750   1.2476   0.01639   0.00892  -0.0824   0.2006   0.5007
   9.000   1.2673   0.01674   0.00930  -0.0810   0.1951   0.5083
   9.250   1.2863   0.01714   0.00970  -0.0796   0.1902   0.5163
   9.500   1.3067   0.01746   0.01009  -0.0784   0.1856   0.5247
   9.750   1.3252   0.01787   0.01053  -0.0770   0.1804   0.5337
  10.000   1.3423   0.01836   0.01102  -0.0754   0.1757   0.5417
  10.250   1.3614   0.01874   0.01147  -0.0741   0.1716   0.5505
  10.500   1.3787   0.01922   0.01198  -0.0725   0.1668   0.5592
  10.750   1.3938   0.01980   0.01259  -0.0708   0.1624   0.5689
  11.000   1.4109   0.02030   0.01315  -0.0694   0.1587   0.5792
  11.250   1.4271   0.02085   0.01376  -0.0679   0.1544   0.5893
  11.500   1.4404   0.02156   0.01450  -0.0661   0.1500   0.5993
  11.750   1.4543   0.02225   0.01525  -0.0645   0.1463   0.6104
  12.000   1.4688   0.02294   0.01600  -0.0630   0.1427   0.6220
  12.250   1.4810   0.02377   0.01690  -0.0614   0.1387   0.6344
  12.500   1.4904   0.02479   0.01797  -0.0596   0.1350   0.6460
  12.750   1.5035   0.02565   0.01891  -0.0583   0.1318   0.6599
  13.000   1.5143   0.02667   0.02002  -0.0569   0.1282   0.6750
  13.250   1.5224   0.02793   0.02134  -0.0554   0.1247   0.6901
  13.500   1.5305   0.02924   0.02274  -0.0541   0.1217   0.7074
  13.750   1.5400   0.03050   0.02411  -0.0530   0.1187   0.7271
  14.000   1.5467   0.03202   0.02573  -0.0518   0.1154   0.7500
  14.500   1.5556   0.03549   0.02947  -0.0497   0.1099   0.8193
  14.750   1.5540   0.03697   0.03122  -0.0475   0.1075   1.0000
  15.000   1.5579   0.03913   0.03342  -0.0470   0.1047   1.0000
  15.250   1.5587   0.04168   0.03600  -0.0467   0.1020   1.0000
  15.500   1.5609   0.04418   0.03856  -0.0465   0.0997   1.0000
  15.750   1.5640   0.04666   0.04111  -0.0465   0.0974   1.0000
  16.000   1.5642   0.04954   0.04404  -0.0466   0.0948   1.0000
  16.250   1.5619   0.05280   0.04735  -0.0470   0.0926   1.0000
  16.500   1.5586   0.05626   0.05087  -0.0475   0.0905   1.0000
  16.750   1.5588   0.05940   0.05409  -0.0480   0.0885   1.0000
  17.000   1.5566   0.06291   0.05768  -0.0488   0.0865   1.0000
  17.250   1.5519   0.06684   0.06166  -0.0498   0.0845   1.0000
  17.500   1.5446   0.07122   0.06611  -0.0510   0.0826   1.0000
  17.750   1.5407   0.07523   0.07019  -0.0522   0.0809   1.0000
  18.000   1.5372   0.07926   0.07431  -0.0535   0.0791   1.0000
  18.250   1.5314   0.08370   0.07883  -0.0551   0.0773   1.0000
  18.500   1.5235   0.08852   0.08372  -0.0569   0.0756   1.0000
<< Back to NREL's S808 Airfoil (s808-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S808 Airfoil (s808-nr)