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NREL's S825 Airfoil (s825-nr) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NREL's S825 Airfoil (s825-nr)
Reynolds number: 50,000
Max Cl/Cd: 32.22 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s825-nr-50000-n5.txt
Download as CSV file: xf-s825-nr-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.4766   0.10940   0.10209  -0.0559   1.0000   0.0389
 -12.000  -0.4919   0.10329   0.09598  -0.0583   1.0000   0.0385
 -11.750  -0.5111   0.09718   0.08984  -0.0607   1.0000   0.0382
 -11.500  -0.5307   0.09160   0.08421  -0.0627   1.0000   0.0379
 -11.250  -0.5503   0.08648   0.07901  -0.0643   1.0000   0.0376
 -11.000  -0.5684   0.08193   0.07438  -0.0654   1.0000   0.0374
 -10.750  -0.5861   0.07766   0.07000  -0.0661   1.0000   0.0374
 -10.500  -0.6002   0.07399   0.06621  -0.0662   1.0000   0.0373
 -10.250  -0.6129   0.07059   0.06268  -0.0657   1.0000   0.0374
 -10.000  -0.6226   0.06762   0.05957  -0.0648   1.0000   0.0375
  -9.750  -0.6300   0.06487   0.05666  -0.0635   1.0000   0.0379
  -9.500  -0.6340   0.06244   0.05404  -0.0617   1.0000   0.0386
  -9.250  -0.6357   0.06025   0.05161  -0.0596   1.0000   0.0397
  -9.000  -0.6192   0.05867   0.04997  -0.0574   1.0000   0.0419
  -8.750  -0.6002   0.05773   0.04899  -0.0549   1.0000   0.0450
  -8.500  -0.5590   0.05760   0.04854  -0.0514   1.0000   0.0495
  -8.250  -0.5380   0.05747   0.04842  -0.0481   1.0000   0.0542
  -8.000  -0.5211   0.05735   0.04826  -0.0448   1.0000   0.0596
  -7.750  -0.5063   0.05737   0.04831  -0.0413   1.0000   0.0655
  -7.500  -0.5010   0.05700   0.04800  -0.0382   1.0000   0.0717
  -7.250  -0.4957   0.05680   0.04787  -0.0347   1.0000   0.0783
  -7.000  -0.4987   0.05624   0.04744  -0.0312   1.0000   0.0851
  -6.750  -0.5034   0.05578   0.04707  -0.0274   1.0000   0.0919
  -6.500  -0.5130   0.05508   0.04653  -0.0237   1.0000   0.0975
  -6.250  -0.5205   0.05417   0.04571  -0.0206   1.0000   0.1063
  -5.750  -0.4857   0.05875   0.05226  -0.0107   0.9987   0.2802
  -5.500  -0.4866   0.04976   0.04275  -0.0301   0.9825   0.3389
  -5.250  -0.4410   0.05297   0.04546  -0.0337   0.9723   0.3950
  -5.000  -0.4050   0.05687   0.04908  -0.0294   0.9638   0.4243
  -4.750  -0.3693   0.05833   0.05027  -0.0295   0.9555   0.4471
  -4.500  -0.3384   0.05939   0.05114  -0.0279   0.9464   0.4650
  -4.250  -0.3099   0.05954   0.05108  -0.0279   0.9364   0.4788
  -4.000  -0.2728   0.05970   0.05104  -0.0268   0.9300   0.4872
  -3.750  -0.2476   0.05840   0.04956  -0.0290   0.9186   0.4881
  -3.500  -0.2226   0.05687   0.04784  -0.0317   0.9069   0.4861
  -3.250  -0.1963   0.05524   0.04602  -0.0351   0.8953   0.4840
  -3.000  -0.1662   0.05354   0.04413  -0.0392   0.8846   0.4823
  -2.750  -0.1313   0.05194   0.04235  -0.0438   0.8756   0.4814
  -2.500  -0.1033   0.05055   0.04081  -0.0468   0.8637   0.4809
  -2.250  -0.0716   0.04913   0.03921  -0.0505   0.8530   0.4803
  -1.750  -0.0001   0.04628   0.03604  -0.0589   0.8338   0.4789
  -1.500   0.0325   0.04516   0.03481  -0.0615   0.8238   0.4784
  -1.250   0.0720   0.04390   0.03343  -0.0653   0.8163   0.4782
  -1.000   0.1039   0.04286   0.03228  -0.0680   0.8053   0.4781
  -0.500   0.1835   0.04048   0.02968  -0.0763   0.7881   0.4791
  -0.250   0.2171   0.03974   0.02889  -0.0783   0.7787   0.4799
   0.000   0.2556   0.03893   0.02803  -0.0808   0.7711   0.4809
   0.250   0.2869   0.03837   0.02743  -0.0825   0.7604   0.4818
   0.500   0.3314   0.03748   0.02649  -0.0861   0.7542   0.4829
   0.750   0.3624   0.03701   0.02600  -0.0879   0.7430   0.4838
   1.000   0.4022   0.03636   0.02530  -0.0912   0.7346   0.4849
   1.500   0.4775   0.03535   0.02424  -0.0970   0.7161   0.4875
   1.750   0.5226   0.03470   0.02356  -0.1010   0.7088   0.4893
   2.000   0.5562   0.03444   0.02329  -0.1036   0.6983   0.4917
   2.250   0.6045   0.03383   0.02263  -0.1085   0.6914   0.4948
   2.500   0.6292   0.03393   0.02281  -0.1085   0.6812   0.4964
   2.750   0.6615   0.03386   0.02280  -0.1098   0.6731   0.4983
   3.000   0.6934   0.03382   0.02283  -0.1111   0.6647   0.5004
   3.250   0.7245   0.03386   0.02293  -0.1126   0.6563   0.5027
   3.500   0.7606   0.03378   0.02289  -0.1150   0.6488   0.5051
   3.750   0.7929   0.03389   0.02308  -0.1170   0.6405   0.5077
   4.000   0.8289   0.03390   0.02315  -0.1193   0.6333   0.5105
   4.250   0.8529   0.03427   0.02367  -0.1191   0.6254   0.5126
   4.500   0.8821   0.03450   0.02406  -0.1197   0.6183   0.5155
   4.750   0.9096   0.03487   0.02456  -0.1204   0.6108   0.5189
   5.000   0.9409   0.03517   0.02497  -0.1219   0.6033   0.5229
   5.250   0.9698   0.03552   0.02548  -0.1228   0.5960   0.5261
   5.500   0.9941   0.03595   0.02610  -0.1226   0.5879   0.5288
   5.750   1.0193   0.03639   0.02670  -0.1227   0.5798   0.5317
   6.000   1.0494   0.03665   0.02710  -0.1235   0.5714   0.5353
   6.250   1.0722   0.03725   0.02787  -0.1235   0.5616   0.5393
   6.500   1.1101   0.03702   0.02780  -0.1247   0.5534   0.5433
   6.750   1.1222   0.03780   0.02881  -0.1226   0.5418   0.5467
   7.000   1.1439   0.03821   0.02938  -0.1219   0.5303   0.5514
   7.250   1.1724   0.03826   0.02961  -0.1220   0.5185   0.5563
   7.500   1.2010   0.03811   0.02962  -0.1215   0.5063   0.5605
   7.750   1.2199   0.03840   0.03010  -0.1201   0.4928   0.5649
   8.000   1.2380   0.03873   0.03059  -0.1187   0.4783   0.5699
   8.250   1.2517   0.03905   0.03115  -0.1164   0.4636   0.5737
   8.500   1.2647   0.03934   0.03163  -0.1139   0.4480   0.5785
   8.750   1.2768   0.03963   0.03205  -0.1115   0.4316   0.5842
   9.000   1.2840   0.04007   0.03267  -0.1083   0.4146   0.5886
   9.250   1.2830   0.04111   0.03391  -0.1046   0.3965   0.5930
   9.500   1.2825   0.04230   0.03527  -0.1013   0.3765   0.5979
   9.750   1.2856   0.04324   0.03631  -0.0984   0.3542   0.6027
  10.000   1.2797   0.04508   0.03835  -0.0953   0.3300   0.6068
  10.250   1.2783   0.04675   0.04005  -0.0928   0.3026   0.6121
  10.500   1.2777   0.04855   0.04180  -0.0906   0.2739   0.6175
  10.750   1.2744   0.05079   0.04389  -0.0885   0.2475   0.6225
  11.000   1.2692   0.05363   0.04659  -0.0869   0.2242   0.6280
  11.250   1.2636   0.05679   0.04968  -0.0857   0.2045   0.6332
  11.500   1.2578   0.06017   0.05305  -0.0848   0.1870   0.6384
  11.750   1.2529   0.06371   0.05656  -0.0843   0.1715   0.6445
  12.000   1.2490   0.06720   0.06006  -0.0839   0.1581   0.6501
  12.250   1.2462   0.07071   0.06358  -0.0837   0.1459   0.6569
  12.500   1.2439   0.07419   0.06704  -0.0836   0.1350   0.6641
  12.750   1.2434   0.07766   0.07067  -0.0836   0.1243   0.6722
  13.000   1.2438   0.08108   0.07420  -0.0837   0.1150   0.6809
  13.500   1.2462   0.08782   0.08122  -0.0840   0.0989   0.7018
  13.750   1.2485   0.09105   0.08453  -0.0842   0.0922   0.7145
  14.000   1.2491   0.09468   0.08842  -0.0847   0.0856   0.7290
  14.250   1.2528   0.09765   0.09146  -0.0848   0.0802   0.7493
  14.500   1.2509   0.10169   0.09590  -0.0855   0.0751   0.7731
  14.750   1.2504   0.10460   0.09897  -0.0854   0.0709   0.8249
  15.000   1.2491   0.10786   0.10242  -0.0860   0.0672   1.0000
  15.250   1.2449   0.11331   0.10814  -0.0884   0.0637   1.0000
  15.500   1.2436   0.11801   0.11295  -0.0906   0.0604   1.0000
  15.750   1.2504   0.12105   0.11587  -0.0916   0.0570   1.0000
  16.000   1.2378   0.12833   0.12351  -0.0956   0.0555   1.0000
  16.250   1.2223   0.13640   0.13189  -0.1003   0.0544   1.0000
  16.500   1.2033   0.14568   0.14143  -0.1062   0.0537   1.0000
  16.750   1.1774   0.15736   0.15336  -0.1140   0.0539   1.0000
  17.000   1.1443   0.17260   0.16875  -0.1242   0.0546   1.0000
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