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 S825 Airfoil (s825-nr) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NREL's S825 Airfoil (s825-nr)
Reynolds number: 500,000
Max Cl/Cd: 93.96 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s825-nr-500000-n5.txt
Download as CSV file: xf-s825-nr-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S825 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
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -0.6675   0.11293   0.11005  -0.0452   1.0000   0.0037
 -15.750  -0.6946   0.10381   0.10076  -0.0492   1.0000   0.0037
 -15.500  -0.7133   0.09699   0.09380  -0.0520   1.0000   0.0037
 -15.250  -0.7234   0.09206   0.08877  -0.0538   1.0000   0.0036
 -15.000  -0.7390   0.08644   0.08299  -0.0557   1.0000   0.0037
 -14.750  -0.7500   0.08179   0.07821  -0.0570   1.0000   0.0036
 -14.500  -0.7604   0.07743   0.07371  -0.0581   1.0000   0.0037
 -14.250  -0.7664   0.07387   0.07003  -0.0588   1.0000   0.0037
 -14.000  -0.7691   0.07015   0.06616  -0.0603   0.9996   0.0037
 -13.750  -0.7674   0.06702   0.06293  -0.0617   0.9991   0.0037
 -13.500  -0.7641   0.06397   0.05975  -0.0632   0.9983   0.0037
 -13.250  -0.7588   0.06127   0.05692  -0.0645   0.9975   0.0037
 -13.000  -0.7526   0.05890   0.05445  -0.0655   0.9967   0.0038
 -12.750  -0.7436   0.05673   0.05218  -0.0666   0.9957   0.0038
 -12.500  -0.7329   0.05471   0.05007  -0.0679   0.9948   0.0038
 -12.250  -0.7220   0.05285   0.04810  -0.0688   0.9940   0.0039
 -12.000  -0.7106   0.05119   0.04638  -0.0695   0.9928   0.0039
 -11.750  -0.7020   0.04948   0.04460  -0.0697   0.9912   0.0040
 -11.500  -0.6895   0.04795   0.04301  -0.0705   0.9894   0.0040
 -11.250  -0.6769   0.04632   0.04134  -0.0715   0.9876   0.0041
 -11.000  -0.6597   0.04485   0.03983  -0.0730   0.9859   0.0042
 -10.750  -0.6392   0.04340   0.03834  -0.0752   0.9843   0.0045
 -10.250  -0.6045   0.04065   0.03552  -0.0778   0.9780   0.0048
 -10.000  -0.5846   0.03930   0.03412  -0.0796   0.9749   0.0049
  -9.750  -0.5621   0.03794   0.03272  -0.0819   0.9726   0.0054
  -9.500  -0.5380   0.03657   0.03130  -0.0847   0.9709   0.0056
  -9.250  -0.5398   0.03536   0.03007  -0.0824   0.9638   0.0056
  -9.000  -0.5249   0.03397   0.02865  -0.0835   0.9598   0.0057
  -8.750  -0.5023   0.03220   0.02686  -0.0868   0.9575   0.0063
  -8.500  -0.5028   0.03067   0.02531  -0.0851   0.9484   0.0067
  -8.250  -0.4770   0.02894   0.02354  -0.0887   0.9454   0.0075
  -8.000  -0.4656   0.02723   0.02179  -0.0895   0.9379   0.0082
  -7.750  -0.4394   0.02518   0.01972  -0.0939   0.9333   0.0093
  -7.500  -0.4043   0.02311   0.01760  -0.0998   0.9310   0.0112
  -7.250  -0.3833   0.02100   0.01545  -0.1030   0.9219   0.0131
  -7.000  -0.3423   0.01858   0.01297  -0.1104   0.9186   0.0178
  -6.750  -0.3050   0.01626   0.01059  -0.1168   0.9123   0.0246
  -6.500  -0.2673   0.01477   0.00908  -0.1216   0.9064   0.0352
  -6.250  -0.2293   0.01368   0.00799  -0.1254   0.9016   0.0504
  -6.000  -0.1938   0.01275   0.00708  -0.1285   0.8944   0.0719
  -5.750  -0.1514   0.01172   0.00613  -0.1328   0.8899   0.1083
  -5.500  -0.1084   0.01056   0.00505  -0.1375   0.8829   0.1628
  -5.250  -0.0560   0.00903   0.00389  -0.1446   0.8774   0.3285
  -5.000  -0.0101   0.00887   0.00367  -0.1483   0.8685   0.3409
  -4.750   0.0445   0.00881   0.00350  -0.1538   0.8567   0.3495
  -4.500   0.0914   0.00882   0.00335  -0.1578   0.8364   0.3549
  -4.250   0.1287   0.00889   0.00320  -0.1597   0.8114   0.3580
  -4.000   0.1592   0.00898   0.00315  -0.1602   0.7869   0.3612
  -3.750   0.1873   0.00910   0.00314  -0.1602   0.7642   0.3635
  -3.500   0.2144   0.00921   0.00312  -0.1601   0.7429   0.3653
  -3.250   0.2411   0.00931   0.00308  -0.1598   0.7230   0.3667
  -3.000   0.2678   0.00939   0.00304  -0.1596   0.7038   0.3680
  -2.750   0.2944   0.00946   0.00299  -0.1594   0.6855   0.3689
  -2.500   0.3211   0.00952   0.00294  -0.1592   0.6684   0.3695
  -2.250   0.3481   0.00958   0.00289  -0.1591   0.6532   0.3702
  -2.000   0.3752   0.00963   0.00286  -0.1590   0.6392   0.3708
  -1.750   0.4024   0.00970   0.00283  -0.1589   0.6260   0.3716
  -1.500   0.4296   0.00976   0.00281  -0.1588   0.6135   0.3723
  -1.250   0.4569   0.00983   0.00280  -0.1588   0.6014   0.3731
  -1.000   0.4844   0.00989   0.00280  -0.1588   0.5895   0.3739
  -0.750   0.5117   0.00994   0.00281  -0.1587   0.5785   0.3748
  -0.500   0.5389   0.01001   0.00284  -0.1587   0.5679   0.3757
  -0.250   0.5666   0.01007   0.00287  -0.1587   0.5581   0.3766
   0.000   0.5941   0.01014   0.00291  -0.1587   0.5494   0.3775
   0.250   0.6216   0.01021   0.00296  -0.1587   0.5408   0.3785
   0.500   0.6493   0.01028   0.00301  -0.1587   0.5330   0.3795
   0.750   0.6767   0.01037   0.00307  -0.1586   0.5249   0.3806
   1.000   0.7043   0.01045   0.00314  -0.1586   0.5174   0.3817
   1.250   0.7316   0.01054   0.00321  -0.1586   0.5099   0.3828
   1.500   0.7592   0.01062   0.00329  -0.1586   0.5037   0.3840
   1.750   0.7868   0.01071   0.00337  -0.1586   0.4974   0.3852
   2.250   0.8416   0.01090   0.00356  -0.1585   0.4861   0.3875
   2.500   0.8688   0.01100   0.00366  -0.1584   0.4801   0.3886
   2.750   0.8960   0.01110   0.00379  -0.1583   0.4750   0.3900
   3.000   0.9236   0.01118   0.00392  -0.1584   0.4702   0.3914
   3.250   0.9507   0.01129   0.00406  -0.1583   0.4649   0.3928
   3.500   0.9773   0.01143   0.00421  -0.1581   0.4579   0.3943
   3.750   1.0030   0.01158   0.00435  -0.1577   0.4474   0.3959
   4.000   1.0291   0.01171   0.00450  -0.1574   0.4370   0.3976
   4.250   1.0547   0.01188   0.00466  -0.1570   0.4289   0.3995
   4.500   1.0809   0.01201   0.00482  -0.1568   0.4207   0.4013
   4.750   1.1064   0.01219   0.00499  -0.1563   0.4125   0.4029
   5.000   1.1322   0.01233   0.00518  -0.1560   0.4039   0.4047
   5.250   1.1576   0.01249   0.00539  -0.1556   0.3956   0.4065
   5.500   1.1823   0.01269   0.00561  -0.1551   0.3855   0.4083
   5.750   1.2071   0.01287   0.00582  -0.1546   0.3737   0.4103
   6.000   1.2309   0.01310   0.00605  -0.1538   0.3592   0.4123
   6.250   1.2531   0.01339   0.00631  -0.1529   0.3405   0.4143
   6.500   1.2731   0.01377   0.00661  -0.1515   0.3120   0.4162
   6.750   1.2888   0.01444   0.00706  -0.1494   0.2691   0.4179
   7.000   1.3026   0.01528   0.00769  -0.1472   0.2258   0.4197
   7.500   1.3336   0.01677   0.00893  -0.1432   0.1658   0.4237
   7.750   1.3496   0.01744   0.00953  -0.1414   0.1442   0.4259
   8.000   1.3647   0.01817   0.01017  -0.1394   0.1234   0.4281
   8.250   1.3795   0.01888   0.01082  -0.1373   0.1060   0.4303
   8.500   1.3941   0.01959   0.01147  -0.1353   0.0916   0.4325
   8.750   1.4089   0.02028   0.01216  -0.1333   0.0800   0.4348
   9.000   1.4232   0.02100   0.01289  -0.1313   0.0700   0.4373
   9.250   1.4375   0.02171   0.01362  -0.1294   0.0619   0.4400
   9.500   1.4508   0.02249   0.01441  -0.1273   0.0544   0.4427
   9.750   1.4624   0.02338   0.01530  -0.1251   0.0472   0.4453
  10.000   1.4748   0.02423   0.01617  -0.1230   0.0414   0.4477
  10.250   1.4852   0.02522   0.01718  -0.1208   0.0359   0.4499
  10.500   1.4961   0.02620   0.01822  -0.1187   0.0315   0.4525
  10.750   1.5057   0.02729   0.01937  -0.1166   0.0279   0.4552
  11.000   1.5153   0.02842   0.02055  -0.1146   0.0246   0.4580
  11.250   1.5231   0.02972   0.02189  -0.1124   0.0218   0.4607
  11.500   1.5311   0.03104   0.02327  -0.1105   0.0192   0.4633
  11.750   1.5371   0.03259   0.02487  -0.1086   0.0168   0.4659
  12.000   1.5444   0.03410   0.02647  -0.1069   0.0149   0.4689
  12.250   1.5490   0.03590   0.02834  -0.1052   0.0132   0.4721
  12.500   1.5545   0.03772   0.03024  -0.1037   0.0118   0.4755
  12.750   1.5588   0.03973   0.03234  -0.1024   0.0105   0.4788
  13.000   1.5619   0.04197   0.03468  -0.1012   0.0094   0.4821
  13.250   1.5660   0.04420   0.03702  -0.1002   0.0085   0.4860
  13.500   1.5685   0.04670   0.03962  -0.0994   0.0077   0.4898
  13.750   1.5696   0.04947   0.04247  -0.0987   0.0070   0.4934
  14.000   1.5721   0.05219   0.04532  -0.0983   0.0065   0.4970
  14.250   1.5735   0.05513   0.04837  -0.0980   0.0059   0.5010
  14.500   1.5737   0.05831   0.05166  -0.0979   0.0055   0.5051
  14.750   1.5728   0.06174   0.05519  -0.0980   0.0050   0.5091
  15.000   1.5723   0.06522   0.05881  -0.0982   0.0047   0.5133
  15.250   1.5716   0.06881   0.06253  -0.0986   0.0044   0.5182
  15.500   1.5702   0.07259   0.06643  -0.0991   0.0041   0.5235
  15.750   1.5680   0.07658   0.07055  -0.0998   0.0039   0.5287
  16.000   1.5650   0.08079   0.07490  -0.1007   0.0036   0.5347
  16.500   1.5566   0.08981   0.08417  -0.1030   0.0033   0.5468
  16.750   1.5534   0.09430   0.08881  -0.1043   0.0032   0.5540
  17.000   1.5495   0.09897   0.09363  -0.1058   0.0030   0.5611
  17.250   1.5452   0.10379   0.09859  -0.1075   0.0029   0.5688
  17.500   1.5405   0.10872   0.10367  -0.1093   0.0028   0.5771
  17.750   1.5356   0.11377   0.10886  -0.1113   0.0027   0.5864
  18.000   1.5303   0.11895   0.11419  -0.1135   0.0026   0.5976
  18.250   1.5250   0.12421   0.11961  -0.1159   0.0026   0.6097
  18.500   1.5191   0.12963   0.12518  -0.1186   0.0025   0.6233
  18.750   1.5130   0.13519   0.13089  -0.1214   0.0024   0.6385
  19.000   1.5061   0.14100   0.13686  -0.1246   0.0024   0.6572
  19.250   1.4977   0.14718   0.14322  -0.1281   0.0022   0.6784
<< Back to NREL's S825 Airfoil (s825-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S825 Airfoil (s825-nr)