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NREL's S825 Airfoil (s825-nr) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NREL's S825 Airfoil (s825-nr)
Reynolds number: 200,000
Max Cl/Cd: 70.13 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s825-nr-200000.txt
Download as CSV file: xf-s825-nr-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4982   0.07420   0.07066  -0.0603   1.0000   0.0302
 -11.000  -0.5177   0.06905   0.06546  -0.0610   1.0000   0.0296
 -10.750  -0.5417   0.06364   0.05996  -0.0616   1.0000   0.0289
 -10.500  -0.6214   0.05345   0.04923  -0.0634   1.0000   0.0251
 -10.250  -0.6173   0.05053   0.04628  -0.0617   1.0000   0.0240
 -10.000  -0.6332   0.04717   0.04285  -0.0604   1.0000   0.0237
  -9.750  -0.7490   0.05656   0.05189  -0.0602   1.0000   0.0255
  -9.500  -0.7411   0.05429   0.04957  -0.0582   1.0000   0.0238
  -9.250  -0.7460   0.05103   0.04619  -0.0580   1.0000   0.0231
  -9.000  -0.7473   0.04749   0.04244  -0.0581   1.0000   0.0223
  -8.750  -0.7448   0.04363   0.03826  -0.0575   1.0000   0.0214
  -8.500  -0.7380   0.04053   0.03484  -0.0558   1.0000   0.0208
  -8.250  -0.7266   0.03852   0.03263  -0.0538   0.9997   0.0208
  -8.000  -0.6952   0.03714   0.03109  -0.0539   0.9954   0.0213
  -7.750  -0.6646   0.03629   0.03012  -0.0533   0.9904   0.0221
  -7.500  -0.6292   0.03543   0.02909  -0.0552   0.9852   0.0241
  -7.250  -0.6020   0.03528   0.02894  -0.0530   0.9795   0.0258
  -7.000  -0.5686   0.03462   0.02834  -0.0548   0.9734   0.0289
  -6.750  -0.5355   0.03428   0.02797  -0.0554   0.9677   0.0323
  -6.500  -0.5017   0.03303   0.02681  -0.0590   0.9607   0.0383
  -6.250  -0.4555   0.03136   0.02518  -0.0660   0.9572   0.0500
  -6.000  -0.4104   0.02775   0.02170  -0.0768   0.9497   0.0703
  -5.750  -0.2928   0.01989   0.01443  -0.1112   0.9568   0.3615
  -5.500  -0.2676   0.02221   0.01690  -0.1078   0.9462   0.3785
  -5.250  -0.2393   0.02410   0.01881  -0.1055   0.9373   0.3901
  -5.000  -0.2227   0.02994   0.02508  -0.0934   0.9306   0.3942
  -4.750  -0.1958   0.03103   0.02609  -0.0918   0.9209   0.4046
  -4.500  -0.1846   0.04703   0.04254  -0.0548   0.9190   0.4377
  -4.250  -0.1565   0.04261   0.03795  -0.0657   0.9080   0.4348
  -4.000  -0.1161   0.04874   0.04414  -0.0496   0.9087   0.4701
  -3.750  -0.0793   0.04688   0.04215  -0.0584   0.9034   0.4804
  -3.500   0.0213   0.02870   0.02413  -0.0605   0.8768   0.4808
  -3.250   0.0495   0.02735   0.02273  -0.0607   0.8695   0.4817
  -3.000   0.0840   0.02598   0.02130  -0.0622   0.8638   0.4831
  -2.750   0.1262   0.02441   0.01964  -0.0661   0.8601   0.4846
  -2.500   0.1552   0.02320   0.01837  -0.0679   0.8486   0.4862
  -2.250   0.1946   0.02184   0.01693  -0.0723   0.8391   0.4883
  -2.000   0.2311   0.02011   0.01506  -0.0817   0.8261   0.4956
  -1.750   0.2548   0.02595   0.02013  -0.1147   0.8461   0.4482
  -1.500   0.2959   0.02518   0.01932  -0.1175   0.8344   0.4475
  -1.250   0.3449   0.02418   0.01824  -0.1225   0.8222   0.4466
  -1.000   0.3957   0.02288   0.01678  -0.1288   0.8073   0.4461
  -0.750   0.4458   0.02140   0.01507  -0.1357   0.7902   0.4464
  -0.500   0.4898   0.02026   0.01371  -0.1407   0.7724   0.4466
  -0.250   0.5309   0.01929   0.01249  -0.1451   0.7548   0.4473
   0.000   0.5677   0.01862   0.01158  -0.1482   0.7375   0.4482
   0.250   0.5982   0.01826   0.01109  -0.1493   0.7206   0.4490
   0.500   0.6268   0.01808   0.01083  -0.1498   0.7049   0.4498
   0.750   0.6551   0.01798   0.01065  -0.1501   0.6906   0.4506
   1.000   0.6833   0.01793   0.01053  -0.1504   0.6774   0.4514
   1.250   0.7107   0.01788   0.01045  -0.1506   0.6646   0.4524
   1.500   0.7384   0.01787   0.01041  -0.1508   0.6528   0.4537
   1.750   0.7673   0.01788   0.01036  -0.1513   0.6422   0.4553
   2.000   0.7966   0.01786   0.01029  -0.1519   0.6320   0.4573
   2.250   0.8258   0.01780   0.01019  -0.1526   0.6222   0.4592
   2.500   0.8578   0.01776   0.01004  -0.1539   0.6142   0.4611
   2.750   0.8874   0.01770   0.00994  -0.1548   0.6050   0.4631
   3.000   0.9176   0.01772   0.00991  -0.1556   0.5975   0.4647
   3.250   0.9446   0.01777   0.01004  -0.1556   0.5896   0.4661
   3.500   0.9740   0.01792   0.01019  -0.1561   0.5833   0.4677
   3.750   1.0002   0.01801   0.01038  -0.1559   0.5756   0.4694
   4.000   1.0301   0.01817   0.01050  -0.1565   0.5689   0.4715
   4.250   1.0556   0.01823   0.01065  -0.1562   0.5602   0.4737
   4.500   1.0846   0.01834   0.01072  -0.1566   0.5520   0.4765
   4.750   1.1108   0.01840   0.01078  -0.1565   0.5421   0.4794
   5.000   1.1361   0.01848   0.01095  -0.1561   0.5335   0.4815
   5.250   1.1617   0.01860   0.01114  -0.1557   0.5249   0.4837
   5.500   1.1863   0.01873   0.01137  -0.1551   0.5161   0.4863
   5.750   1.2134   0.01886   0.01149  -0.1551   0.5076   0.4891
   6.000   1.2370   0.01896   0.01170  -0.1544   0.4980   0.4922
   6.250   1.2629   0.01908   0.01184  -0.1541   0.4890   0.4951
   6.500   1.2854   0.01915   0.01203  -0.1531   0.4787   0.4974
   6.750   1.3069   0.01927   0.01228  -0.1519   0.4678   0.5001
   7.000   1.3287   0.01940   0.01248  -0.1507   0.4564   0.5033
   7.250   1.3502   0.01954   0.01265  -0.1495   0.4443   0.5069
   7.500   1.3697   0.01967   0.01285  -0.1480   0.4306   0.5105
   7.750   1.3866   0.01980   0.01313  -0.1459   0.4156   0.5134
   8.000   1.4019   0.01999   0.01343  -0.1436   0.3979   0.5169
   8.250   1.4156   0.02022   0.01375  -0.1410   0.3766   0.5209
   8.500   1.4251   0.02056   0.01406  -0.1377   0.3502   0.5248
   8.750   1.4298   0.02108   0.01454  -0.1336   0.3118   0.5275
   9.000   1.4283   0.02217   0.01541  -0.1289   0.2636   0.5302
   9.500   1.4241   0.02524   0.01803  -0.1204   0.1870   0.5367
   9.750   1.4238   0.02688   0.01950  -0.1167   0.1600   0.5402
  10.000   1.4238   0.02852   0.02109  -0.1133   0.1385   0.5430
  10.250   1.4229   0.03032   0.02285  -0.1100   0.1219   0.5462
  10.500   1.4226   0.03221   0.02471  -0.1071   0.1081   0.5501
  10.750   1.4237   0.03413   0.02663  -0.1046   0.0963   0.5545
  11.000   1.4250   0.03611   0.02869  -0.1023   0.0864   0.5581
  11.250   1.4228   0.03850   0.03113  -0.1001   0.0789   0.5619
  11.500   1.4231   0.04082   0.03354  -0.0983   0.0718   0.5667
  11.750   1.4222   0.04344   0.03623  -0.0968   0.0658   0.5712
  12.000   1.4226   0.04601   0.03890  -0.0956   0.0603   0.5754
  12.250   1.4194   0.04912   0.04208  -0.0944   0.0558   0.5800
  12.500   1.4225   0.05172   0.04480  -0.0938   0.0508   0.5858
  12.750   1.4170   0.05532   0.04842  -0.0931   0.0471   0.5897
  13.000   1.4204   0.05811   0.05140  -0.0928   0.0433   0.5957
  13.250   1.4215   0.06123   0.05462  -0.0928   0.0398   0.6019
  13.500   1.4168   0.06508   0.05849  -0.0924   0.0368   0.6069
  13.750   1.4200   0.06819   0.06181  -0.0926   0.0339   0.6148
  14.000   1.4205   0.07164   0.06539  -0.0930   0.0314   0.6218
  14.250   1.4176   0.07550   0.06922  -0.0927   0.0289   0.6297
  14.500   1.4194   0.07901   0.07303  -0.0933   0.0270   0.6385
  14.750   1.4197   0.08272   0.07689  -0.0940   0.0250   0.6489
  15.000   1.4190   0.08655   0.08079  -0.0949   0.0234   0.6610
  15.250   1.4182   0.09035   0.08473  -0.0951   0.0217   0.6738
  15.500   1.4180   0.09428   0.08891  -0.0960   0.0204   0.6909
  15.750   1.4178   0.09816   0.09300  -0.0969   0.0193   0.7142
  16.000   1.4174   0.10198   0.09703  -0.0978   0.0184   0.7562
  16.250   1.4135   0.10471   0.10002  -0.0973   0.0177   1.0000
  16.500   1.4138   0.10871   0.10410  -0.0978   0.0169   1.0000
  16.750   1.4090   0.11380   0.10941  -0.1000   0.0163   1.0000
  17.000   1.4035   0.11906   0.11488  -0.1025   0.0157   1.0000
  17.250   1.3990   0.12418   0.12017  -0.1049   0.0153   1.0000
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