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 S834 Airfoil (s834-nr) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NREL's S834 Airfoil (s834-nr)
Reynolds number: 500,000
Max Cl/Cd: 74.36 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s834-nr-500000-n5.txt
Download as CSV file: xf-s834-nr-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S834 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
  ------ -------- --------- --------- -------- -------- --------
 -17.750  -0.8555   0.09565   0.09198  -0.0649   1.0000   0.0042
 -17.500  -0.8742   0.08953   0.08576  -0.0673   1.0000   0.0042
 -17.250  -0.9010   0.08220   0.07829  -0.0702   1.0000   0.0041
 -17.000  -0.9182   0.07669   0.07267  -0.0721   1.0000   0.0041
 -16.750  -0.9367   0.07112   0.06698  -0.0740   1.0000   0.0041
 -16.500  -0.9563   0.06561   0.06135  -0.0758   1.0000   0.0042
 -16.250  -0.9742   0.06055   0.05617  -0.0772   1.0000   0.0042
 -16.000  -0.9886   0.05621   0.05171  -0.0782   1.0000   0.0041
 -15.750  -1.0000   0.05250   0.04790  -0.0786   1.0000   0.0044
 -15.500  -1.0144   0.04864   0.04391  -0.0789   1.0000   0.0044
 -15.250  -1.0199   0.04531   0.04047  -0.0797   0.9996   0.0047
 -15.000  -1.0165   0.04209   0.03712  -0.0820   0.9984   0.0048
 -14.750  -1.0123   0.03910   0.03400  -0.0840   0.9969   0.0048
 -14.500  -1.0044   0.03665   0.03142  -0.0857   0.9954   0.0052
 -14.250  -0.9961   0.03425   0.02890  -0.0873   0.9939   0.0055
 -14.000  -0.9893   0.03211   0.02666  -0.0881   0.9920   0.0060
 -13.750  -0.9795   0.03038   0.02482  -0.0886   0.9898   0.0062
 -13.500  -0.9679   0.02876   0.02312  -0.0892   0.9876   0.0069
 -13.250  -0.9524   0.02743   0.02170  -0.0900   0.9858   0.0075
 -13.000  -0.9356   0.02614   0.02032  -0.0908   0.9843   0.0084
 -12.750  -0.9175   0.02486   0.01898  -0.0918   0.9830   0.0091
 -12.500  -0.9030   0.02383   0.01789  -0.0915   0.9805   0.0100
 -12.250  -0.8893   0.02291   0.01689  -0.0908   0.9771   0.0106
 -12.000  -0.8701   0.02205   0.01597  -0.0910   0.9747   0.0121
 -11.750  -0.8493   0.02114   0.01498  -0.0916   0.9729   0.0134
 -11.500  -0.8256   0.02035   0.01417  -0.0925   0.9715   0.0159
 -11.250  -0.8003   0.01957   0.01332  -0.0935   0.9704   0.0177
 -11.000  -0.7864   0.01890   0.01265  -0.0922   0.9665   0.0205
 -10.750  -0.7684   0.01834   0.01204  -0.0914   0.9628   0.0228
 -10.500  -0.7467   0.01767   0.01135  -0.0914   0.9602   0.0260
 -10.250  -0.7233   0.01705   0.01071  -0.0916   0.9582   0.0297
 -10.000  -0.6983   0.01649   0.01011  -0.0920   0.9566   0.0335
  -9.750  -0.6936   0.01612   0.00970  -0.0880   0.9492   0.0367
  -9.500  -0.6734   0.01566   0.00921  -0.0871   0.9459   0.0408
  -9.250  -0.6507   0.01517   0.00871  -0.0868   0.9437   0.0461
  -9.000  -0.6366   0.01482   0.00835  -0.0846   0.9385   0.0518
  -8.750  -0.6188   0.01442   0.00795  -0.0831   0.9339   0.0584
  -8.500  -0.5956   0.01402   0.00754  -0.0827   0.9312   0.0656
  -8.250  -0.5716   0.01355   0.00710  -0.0825   0.9291   0.0761
  -8.000  -0.5580   0.01326   0.00681  -0.0800   0.9226   0.0845
  -7.750  -0.5356   0.01291   0.00646  -0.0793   0.9190   0.0940
  -7.500  -0.5107   0.01254   0.00610  -0.0791   0.9163   0.1043
  -7.250  -0.4903   0.01223   0.00581  -0.0779   0.9119   0.1157
  -7.000  -0.4694   0.01192   0.00553  -0.0769   0.9071   0.1282
  -6.750  -0.4448   0.01158   0.00522  -0.0766   0.9038   0.1428
  -6.500  -0.4179   0.01124   0.00490  -0.0768   0.9013   0.1581
  -6.250  -0.3981   0.01101   0.00470  -0.0754   0.8953   0.1705
  -6.000  -0.3732   0.01072   0.00444  -0.0751   0.8912   0.1870
  -5.750  -0.3460   0.01041   0.00417  -0.0753   0.8881   0.2048
  -5.500  -0.3237   0.01019   0.00398  -0.0744   0.8827   0.2212
  -5.250  -0.2984   0.00995   0.00377  -0.0742   0.8781   0.2371
  -5.000  -0.2710   0.00970   0.00355  -0.0743   0.8746   0.2566
  -4.750  -0.2469   0.00951   0.00339  -0.0738   0.8695   0.2741
  -4.500  -0.2217   0.00930   0.00323  -0.0735   0.8647   0.2924
  -4.250  -0.1944   0.00910   0.00305  -0.0736   0.8609   0.3116
  -4.000  -0.1693   0.00893   0.00293  -0.0732   0.8562   0.3309
  -3.750  -0.1441   0.00877   0.00281  -0.0729   0.8513   0.3497
  -3.500  -0.1171   0.00859   0.00267  -0.0729   0.8472   0.3708
  -3.250  -0.0912   0.00845   0.00257  -0.0727   0.8427   0.3906
  -3.000  -0.0661   0.00831   0.00249  -0.0724   0.8376   0.4100
  -2.750  -0.0392   0.00817   0.00239  -0.0723   0.8333   0.4315
  -2.500  -0.0128   0.00806   0.00232  -0.0722   0.8290   0.4513
  -2.250   0.0125   0.00794   0.00226  -0.0718   0.8237   0.4714
  -2.000   0.0395   0.00783   0.00219  -0.0718   0.8192   0.4927
  -1.750   0.0658   0.00772   0.00214  -0.0717   0.8147   0.5136
  -1.500   0.0915   0.00763   0.00211  -0.0713   0.8093   0.5346
  -1.250   0.1186   0.00753   0.00207  -0.0713   0.8045   0.5557
  -1.000   0.1447   0.00745   0.00205  -0.0711   0.7995   0.5763
  -0.750   0.1708   0.00738   0.00204  -0.0708   0.7938   0.5970
  -0.500   0.1982   0.00731   0.00201  -0.0708   0.7889   0.6180
  -0.250   0.2236   0.00725   0.00203  -0.0704   0.7825   0.6383
   0.000   0.2503   0.00720   0.00203  -0.0702   0.7759   0.6579
   0.250   0.2758   0.00716   0.00205  -0.0697   0.7679   0.6772
   0.500   0.3024   0.00714   0.00205  -0.0695   0.7599   0.6957
   0.750   0.3274   0.00713   0.00209  -0.0689   0.7504   0.7129
   1.000   0.3529   0.00712   0.00213  -0.0684   0.7412   0.7293
   1.500   0.4034   0.00716   0.00222  -0.0673   0.7207   0.7587
   1.750   0.4283   0.00720   0.00228  -0.0667   0.7092   0.7720
   2.000   0.4528   0.00726   0.00235  -0.0660   0.6972   0.7847
   2.250   0.4769   0.00733   0.00244  -0.0652   0.6848   0.7958
   2.500   0.5002   0.00742   0.00253  -0.0642   0.6704   0.8059
   2.750   0.5230   0.00753   0.00262  -0.0631   0.6545   0.8158
   3.000   0.5449   0.00766   0.00274  -0.0619   0.6374   0.8251
   3.250   0.5662   0.00781   0.00286  -0.0605   0.6199   0.8332
   3.500   0.5867   0.00798   0.00297  -0.0590   0.6000   0.8420
   3.750   0.6057   0.00817   0.00312  -0.0571   0.5787   0.8489
   4.000   0.6239   0.00839   0.00327  -0.0552   0.5540   0.8570
   4.250   0.6379   0.00863   0.00343  -0.0524   0.5264   0.8634
   4.500   0.6511   0.00891   0.00360  -0.0495   0.4933   0.8710
   4.750   0.6608   0.00929   0.00384  -0.0458   0.4555   0.8771
   5.000   0.6730   0.00972   0.00412  -0.0429   0.4170   0.8842
   5.250   0.6852   0.01014   0.00442  -0.0400   0.3824   0.8897
   5.500   0.6972   0.01064   0.00475  -0.0371   0.3429   0.8962
   5.750   0.7113   0.01106   0.00506  -0.0347   0.3107   0.9019
   6.000   0.7253   0.01148   0.00538  -0.0322   0.2812   0.9077
   6.250   0.7405   0.01193   0.00571  -0.0301   0.2510   0.9137
   6.500   0.7536   0.01235   0.00603  -0.0275   0.2236   0.9191
   6.750   0.7684   0.01278   0.00637  -0.0254   0.1993   0.9251
   7.000   0.7830   0.01319   0.00673  -0.0231   0.1767   0.9307
   7.250   0.7969   0.01363   0.00709  -0.0209   0.1551   0.9369
   7.500   0.8109   0.01411   0.00748  -0.0187   0.1322   0.9430
   7.750   0.8247   0.01458   0.00787  -0.0165   0.1126   0.9495
   8.000   0.8402   0.01506   0.00829  -0.0147   0.0949   0.9564
   8.250   0.8587   0.01554   0.00874  -0.0135   0.0817   0.9635
   8.500   0.8801   0.01607   0.00924  -0.0131   0.0694   0.9709
   8.750   0.9039   0.01665   0.00980  -0.0133   0.0577   0.9789
   9.250   0.9437   0.01789   0.01095  -0.0123   0.0376   1.0000
   9.500   0.9599   0.01855   0.01157  -0.0110   0.0304   1.0000
   9.750   0.9767   0.01918   0.01220  -0.0099   0.0250   1.0000
  10.000   0.9928   0.01986   0.01287  -0.0087   0.0211   1.0000
  10.250   1.0093   0.02051   0.01354  -0.0076   0.0181   1.0000
  10.500   1.0244   0.02126   0.01431  -0.0064   0.0159   1.0000
  10.750   1.0399   0.02199   0.01506  -0.0052   0.0133   1.0000
  11.000   1.0540   0.02281   0.01589  -0.0039   0.0113   1.0000
  11.250   1.0683   0.02362   0.01675  -0.0026   0.0102   1.0000
  11.500   1.0825   0.02445   0.01763  -0.0014   0.0091   1.0000
  11.750   1.0953   0.02539   0.01860  -0.0001   0.0081   1.0000
  12.000   1.1074   0.02639   0.01966   0.0012   0.0077   1.0000
  12.250   1.1195   0.02741   0.02074   0.0025   0.0069   1.0000
  12.500   1.1312   0.02847   0.02187   0.0037   0.0063   1.0000
  12.750   1.1420   0.02961   0.02310   0.0049   0.0058   1.0000
  13.000   1.1516   0.03087   0.02441   0.0062   0.0054   1.0000
  13.250   1.1579   0.03243   0.02603   0.0076   0.0048   1.0000
  13.500   1.1663   0.03383   0.02753   0.0088   0.0049   1.0000
  13.750   1.1744   0.03531   0.02910   0.0098   0.0046   1.0000
  14.000   1.1808   0.03697   0.03085   0.0109   0.0045   1.0000
  14.250   1.1868   0.03870   0.03268   0.0119   0.0042   1.0000
  14.500   1.1920   0.04057   0.03465   0.0127   0.0041   1.0000
  14.750   1.1965   0.04256   0.03673   0.0135   0.0039   1.0000
  15.000   1.1986   0.04484   0.03912   0.0141   0.0038   1.0000
  15.250   1.2013   0.04716   0.04155   0.0146   0.0038   1.0000
  15.500   1.2022   0.04975   0.04424   0.0149   0.0037   1.0000
  15.750   1.2029   0.05247   0.04709   0.0151   0.0037   1.0000
  16.000   1.2025   0.05539   0.05012   0.0150   0.0036   1.0000
  16.250   1.2000   0.05870   0.05355   0.0147   0.0036   1.0000
  16.500   1.1977   0.06213   0.05711   0.0141   0.0036   1.0000
  16.750   1.1926   0.06608   0.06117   0.0132   0.0034   1.0000
  17.000   1.1865   0.07030   0.06551   0.0120   0.0033   1.0000
  17.250   1.1763   0.07536   0.07071   0.0103   0.0032   1.0000
  17.500   1.1702   0.07996   0.07544   0.0085   0.0032   1.0000
  17.750   1.1617   0.08516   0.08077   0.0063   0.0033   1.0000
  18.000   1.1506   0.09094   0.08670   0.0036   0.0033   1.0000
  18.250   1.1320   0.09829   0.09420   0.0000   0.0032   1.0000
  18.500   1.1256   0.10367   0.09971  -0.0028   0.0032   1.0000
  18.750   1.1069   0.11146   0.10765  -0.0070   0.0032   1.0000
  19.000   1.0979   0.11751   0.11383  -0.0103   0.0032   1.0000
  19.250   1.0828   0.12491   0.12137  -0.0145   0.0033   1.0000
<< Back to NREL's S834 Airfoil (s834-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S834 Airfoil (s834-nr)