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NREL's S803 Airfoil (s803-nr) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NREL's S803 Airfoil (s803-nr)
Reynolds number: 50,000
Max Cl/Cd: 37.14 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s803-nr-50000-n5.txt
Download as CSV file: xf-s803-nr-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S803 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3604   0.09933   0.09241  -0.0455   1.0000   0.0601
  -8.500  -0.3639   0.09627   0.08944  -0.0451   1.0000   0.0588
  -8.250  -0.3705   0.09324   0.08652  -0.0447   1.0000   0.0576
  -8.000  -0.3814   0.09020   0.08361  -0.0442   1.0000   0.0566
  -7.750  -0.3964   0.08734   0.08090  -0.0432   1.0000   0.0555
  -7.500  -0.4156   0.08423   0.07794  -0.0426   1.0000   0.0545
  -7.000  -0.4628   0.07206   0.06574  -0.0512   1.0000   0.0506
  -6.750  -0.4676   0.06878   0.06243  -0.0513   1.0000   0.0503
  -6.500  -0.4518   0.06294   0.05631  -0.0578   0.9939   0.0502
  -6.000  -0.3998   0.05272   0.04543  -0.0699   0.9779   0.0526
  -5.750  -0.3687   0.04834   0.04062  -0.0750   0.9709   0.0536
  -5.500  -0.3360   0.04397   0.03565  -0.0795   0.9636   0.0539
  -5.250  -0.3018   0.04044   0.03156  -0.0831   0.9569   0.0547
  -5.000  -0.2663   0.03758   0.02819  -0.0862   0.9505   0.0562
  -4.750  -0.2319   0.03536   0.02547  -0.0885   0.9437   0.0598
  -4.500  -0.1959   0.03338   0.02291  -0.0904   0.9372   0.0628
  -4.250  -0.1640   0.03171   0.02114  -0.0916   0.9307   0.0656
  -4.000  -0.1324   0.03045   0.01972  -0.0924   0.9237   0.0692
  -3.750  -0.0991   0.02940   0.01841  -0.0932   0.9177   0.0762
  -3.500  -0.0701   0.02847   0.01747  -0.0937   0.9099   0.0850
  -3.250  -0.0337   0.02740   0.01634  -0.0955   0.9051   0.0993
  -3.000  -0.0060   0.02650   0.01554  -0.0961   0.8964   0.1277
  -2.750   0.0345   0.02482   0.01462  -0.1001   0.8919   0.2462
  -2.500   0.0574   0.02366   0.01492  -0.0993   0.8846   0.4984
  -2.250   0.0801   0.02401   0.01539  -0.0968   0.8776   0.6495
  -2.000   0.0979   0.02439   0.01567  -0.0937   0.8692   0.7111
  -1.750   0.1186   0.02458   0.01571  -0.0909   0.8625   0.7560
  -1.500   0.1337   0.02471   0.01573  -0.0875   0.8544   0.7895
  -1.250   0.1529   0.02468   0.01557  -0.0849   0.8478   0.8211
  -1.000   0.1699   0.02465   0.01541  -0.0822   0.8406   0.8494
  -0.750   0.1885   0.02453   0.01517  -0.0799   0.8335   0.8773
  -0.500   0.2161   0.02426   0.01477  -0.0791   0.8291   0.9061
  -0.250   0.2374   0.02431   0.01473  -0.0782   0.8205   0.9339
   0.000   0.2843   0.02420   0.01446  -0.0820   0.8166   0.9600
   0.250   0.3223   0.02431   0.01444  -0.0849   0.8098   1.0000
   0.500   0.3527   0.02455   0.01454  -0.0864   0.8033   1.0000
   0.750   0.3924   0.02466   0.01450  -0.0892   0.7995   1.0000
   1.000   0.4140   0.02521   0.01496  -0.0894   0.7908   1.0000
   1.250   0.4511   0.02541   0.01507  -0.0917   0.7861   1.0000
   1.500   0.4806   0.02585   0.01543  -0.0930   0.7797   1.0000
   1.750   0.5106   0.02627   0.01580  -0.0943   0.7731   1.0000
   2.000   0.5496   0.02643   0.01591  -0.0966   0.7691   1.0000
   2.250   0.5710   0.02716   0.01662  -0.0967   0.7603   1.0000
   2.500   0.6070   0.02740   0.01683  -0.0985   0.7553   1.0000
   2.750   0.6327   0.02800   0.01743  -0.0990   0.7478   1.0000
   3.000   0.6642   0.02837   0.01783  -0.1001   0.7413   1.0000
   3.250   0.6971   0.02869   0.01816  -0.1013   0.7354   1.0000
   3.500   0.7215   0.02930   0.01881  -0.1014   0.7267   1.0000
   3.750   0.7625   0.02925   0.01883  -0.1034   0.7223   1.0000
   4.000   0.7794   0.03011   0.01975  -0.1024   0.7113   1.0000
   4.250   0.8106   0.03038   0.02009  -0.1030   0.7037   1.0000
   4.500   0.8395   0.03067   0.02047  -0.1033   0.6946   1.0000
   4.750   0.8633   0.03115   0.02107  -0.1028   0.6841   1.0000
   5.000   0.9055   0.03071   0.02074  -0.1043   0.6768   1.0000
   5.250   0.9270   0.03113   0.02128  -0.1033   0.6639   1.0000
   5.500   0.9526   0.03128   0.02159  -0.1026   0.6511   1.0000
   5.750   0.9814   0.03118   0.02162  -0.1021   0.6376   1.0000
   6.000   1.0105   0.03095   0.02152  -0.1015   0.6229   1.0000
   6.250   1.0382   0.03069   0.02144  -0.1005   0.6066   1.0000
   6.500   1.0654   0.03036   0.02125  -0.0994   0.5887   1.0000
   6.750   1.0946   0.02984   0.02084  -0.0984   0.5692   1.0000
   7.000   1.1055   0.03024   0.02140  -0.0955   0.5457   1.0000
   7.250   1.1225   0.03026   0.02157  -0.0932   0.5200   1.0000
   7.500   1.1336   0.03053   0.02195  -0.0902   0.4903   1.0000
   7.750   1.1434   0.03093   0.02242  -0.0871   0.4549   1.0000
   8.000   1.1574   0.03116   0.02255  -0.0844   0.4096   1.0000
   8.250   1.1694   0.03176   0.02279  -0.0815   0.3585   1.0000
   8.500   1.1739   0.03314   0.02387  -0.0785   0.3131   1.0000
   8.750   1.1753   0.03495   0.02542  -0.0756   0.2752   1.0000
   9.000   1.1766   0.03694   0.02722  -0.0732   0.2448   1.0000
   9.250   1.1787   0.03903   0.02917  -0.0710   0.2193   1.0000
   9.500   1.1814   0.04118   0.03120  -0.0692   0.1984   1.0000
   9.750   1.1860   0.04332   0.03322  -0.0676   0.1812   1.0000
  10.000   1.1925   0.04539   0.03528  -0.0662   0.1655   1.0000
  10.250   1.2006   0.04742   0.03729  -0.0649   0.1526   1.0000
  10.500   1.2111   0.04935   0.03928  -0.0638   0.1406   1.0000
  10.750   1.2229   0.05125   0.04127  -0.0627   0.1298   1.0000
  11.000   1.2375   0.05304   0.04313  -0.0618   0.1209   1.0000
  11.250   1.2530   0.05479   0.04492  -0.0609   0.1127   1.0000
  11.500   1.2689   0.05670   0.04707  -0.0601   0.1049   1.0000
  11.750   1.2871   0.05844   0.04881  -0.0593   0.0988   1.0000
  12.000   1.3030   0.06071   0.05140  -0.0586   0.0931   1.0000
  12.250   1.3137   0.06304   0.05389  -0.0578   0.0881   1.0000
  12.500   1.3295   0.06533   0.05623  -0.0572   0.0838   1.0000
  12.750   1.3342   0.06867   0.06001  -0.0565   0.0806   1.0000
  13.000   1.3362   0.07198   0.06361  -0.0559   0.0775   1.0000
  13.250   1.3401   0.07491   0.06670  -0.0554   0.0745   1.0000
  13.500   1.3445   0.07819   0.07009  -0.0551   0.0720   1.0000
  13.750   1.3309   0.08321   0.07554  -0.0552   0.0707   1.0000
  14.000   1.3149   0.08872   0.08142  -0.0559   0.0697   1.0000
  14.250   1.2956   0.09485   0.08789  -0.0574   0.0690   1.0000
  14.500   1.2726   0.10179   0.09514  -0.0598   0.0685   1.0000
  14.750   1.2449   0.10994   0.10356  -0.0635   0.0685   1.0000
  15.000   1.2118   0.11994   0.11380  -0.0691   0.0689   1.0000
  15.250   1.1728   0.13263   0.12663  -0.0772   0.0698   1.0000
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