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=100,000 Ncrit=9


Details Polar file
Airfoil: NREL's S834 Airfoil (s834-nr)
Reynolds number: 100,000
Max Cl/Cd: 47.4 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s834-nr-100000.txt
Download as CSV file: xf-s834-nr-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.3913   0.13311   0.12838  -0.0412   1.0000   0.1599
 -12.750  -0.8070   0.06644   0.06074  -0.0783   1.0000   0.0534
 -12.500  -0.8325   0.06326   0.05743  -0.0760   1.0000   0.0533
 -12.250  -0.8586   0.06057   0.05459  -0.0726   1.0000   0.0533
 -12.000  -0.8852   0.05835   0.05222  -0.0682   1.0000   0.0533
 -11.750  -0.9121   0.05662   0.05034  -0.0627   1.0000   0.0533
 -11.500  -0.9383   0.05509   0.04865  -0.0565   1.0000   0.0534
 -11.250  -0.9583   0.05214   0.04554  -0.0516   1.0000   0.0539
 -11.000  -0.9591   0.04977   0.04325  -0.0489   1.0000   0.0565
 -10.750  -0.9633   0.04865   0.04210  -0.0451   1.0000   0.0592
 -10.500  -0.9721   0.04679   0.04002  -0.0408   1.0000   0.0611
 -10.250  -0.9806   0.04475   0.03765  -0.0363   1.0000   0.0632
 -10.000  -0.9866   0.04270   0.03516  -0.0319   1.0000   0.0651
  -9.750  -0.9803   0.04008   0.03250  -0.0295   1.0000   0.0686
  -9.500  -0.9747   0.03892   0.03126  -0.0267   1.0000   0.0733
  -9.250  -0.9717   0.03748   0.02939  -0.0232   1.0000   0.0780
  -9.000  -0.9586   0.03549   0.02751  -0.0216   1.0000   0.0833
  -8.750  -0.9501   0.03432   0.02606  -0.0189   1.0000   0.0900
  -8.500  -0.9377   0.03289   0.02470  -0.0170   1.0000   0.0975
  -8.250  -0.9263   0.03162   0.02315  -0.0146   1.0000   0.1060
  -8.000  -0.9132   0.03062   0.02217  -0.0128   1.0000   0.1159
  -7.750  -0.8994   0.02950   0.02108  -0.0109   1.0000   0.1264
  -7.500  -0.8852   0.02844   0.02000  -0.0091   1.0000   0.1388
  -7.250  -0.8712   0.02758   0.01913  -0.0073   1.0000   0.1529
  -7.000  -0.8564   0.02674   0.01830  -0.0056   1.0000   0.1687
  -6.750  -0.8412   0.02600   0.01752  -0.0040   1.0000   0.1869
  -6.500  -0.8256   0.02528   0.01687  -0.0025   1.0000   0.2061
  -6.250  -0.8094   0.02464   0.01631  -0.0010   1.0000   0.2264
  -6.000  -0.7928   0.02406   0.01573   0.0004   1.0000   0.2492
  -5.750  -0.7759   0.02357   0.01527   0.0017   1.0000   0.2736
  -5.500  -0.7587   0.02310   0.01493   0.0030   1.0000   0.2985
  -5.250  -0.7411   0.02268   0.01460   0.0042   1.0000   0.3250
  -5.000  -0.7233   0.02232   0.01433   0.0054   1.0000   0.3531
  -4.750  -0.7051   0.02201   0.01410   0.0066   1.0000   0.3821
  -4.500  -0.6869   0.02175   0.01391   0.0078   1.0000   0.4123
  -4.250  -0.6685   0.02153   0.01380   0.0090   1.0000   0.4434
  -4.000  -0.6501   0.02136   0.01373   0.0102   1.0000   0.4759
  -3.750  -0.6316   0.02123   0.01371   0.0114   1.0000   0.5091
  -3.500  -0.6067   0.02135   0.01397   0.0115   0.9976   0.5449
  -3.250  -0.5695   0.02190   0.01463   0.0094   0.9900   0.5868
  -3.000  -0.5343   0.02250   0.01535   0.0078   0.9833   0.6278
  -2.750  -0.5059   0.02283   0.01578   0.0077   0.9757   0.6656
  -2.250  -0.4505   0.02388   0.01699   0.0082   0.9621   0.7346
  -2.000  -0.4180   0.02481   0.01793   0.0077   0.9560   0.7673
  -1.750  -0.4011   0.02515   0.01830   0.0103   0.9483   0.7938
  -1.250  -0.3558   0.02650   0.01958   0.0134   0.9345   0.8447
  -1.000  -0.3237   0.02744   0.02045   0.0132   0.9289   0.8695
  -0.750  -0.3054   0.02775   0.02073   0.0154   0.9208   0.8909
  -0.500  -0.2637   0.02858   0.02146   0.0131   0.9156   0.9124
  -0.250  -0.2247   0.02910   0.02192   0.0108   0.9085   0.9293
   0.000  -0.1618   0.02996   0.02267   0.0038   0.9038   0.9423
   0.250  -0.0872   0.03083   0.02347  -0.0058   0.8994   0.9503
   0.500  -0.0252   0.03135   0.02393  -0.0132   0.8933   0.9601
   0.750   0.0456   0.03186   0.02440  -0.0221   0.8892   0.9699
   1.000   0.1056   0.03217   0.02470  -0.0294   0.8827   0.9794
   1.250   0.1735   0.03234   0.02487  -0.0381   0.8772   0.9877
   1.500   0.2488   0.03241   0.02495  -0.0479   0.8739   0.9954
   1.750   0.2766   0.03238   0.02493  -0.0495   0.8636   1.0000
   2.000   0.2927   0.03230   0.02486  -0.0485   0.8539   1.0000
   2.250   0.3277   0.03208   0.02466  -0.0504   0.8468   1.0000
   2.500   0.3368   0.03203   0.02461  -0.0480   0.8352   1.0000
   2.750   0.3537   0.03196   0.02456  -0.0467   0.8250   1.0000
   3.000   0.3950   0.03159   0.02424  -0.0491   0.8183   1.0000
   3.250   0.4053   0.03154   0.02422  -0.0465   0.8064   1.0000
   3.500   0.4228   0.03140   0.02412  -0.0450   0.7953   1.0000
   3.750   0.4748   0.03066   0.02348  -0.0485   0.7896   1.0000
   4.000   0.4885   0.03047   0.02334  -0.0461   0.7773   1.0000
   4.250   0.5074   0.03018   0.02310  -0.0444   0.7656   1.0000
   4.500   0.5718   0.02879   0.02186  -0.0492   0.7611   1.0000
   4.750   0.5901   0.02832   0.02149  -0.0470   0.7487   1.0000
   5.000   0.6174   0.02754   0.02080  -0.0460   0.7374   1.0000
   5.250   0.7060   0.02507   0.01858  -0.0541   0.7334   1.0000
   5.500   0.7482   0.02383   0.01751  -0.0552   0.7206   1.0000
   5.750   0.8098   0.02215   0.01603  -0.0594   0.7058   1.0000
   6.000   0.8511   0.02094   0.01493  -0.0603   0.6860   1.0000
   6.250   0.8795   0.02008   0.01418  -0.0591   0.6614   1.0000
   6.500   0.8949   0.01960   0.01372  -0.0558   0.6331   1.0000
   6.750   0.9067   0.01928   0.01337  -0.0520   0.6000   1.0000
   7.000   0.9092   0.01918   0.01318  -0.0466   0.5637   1.0000
   7.250   0.9064   0.01920   0.01306  -0.0404   0.5260   1.0000
   7.500   0.9020   0.01936   0.01302  -0.0340   0.4858   1.0000
   7.750   0.8975   0.01973   0.01313  -0.0280   0.4425   1.0000
   8.000   0.8954   0.02036   0.01347  -0.0227   0.3978   1.0000
   8.250   0.8949   0.02120   0.01402  -0.0180   0.3538   1.0000
   8.500   0.8951   0.02219   0.01472  -0.0138   0.3123   1.0000
   8.750   0.8967   0.02328   0.01562  -0.0101   0.2733   1.0000
   9.000   0.8993   0.02449   0.01658  -0.0066   0.2376   1.0000
   9.250   0.9026   0.02580   0.01768  -0.0035   0.2044   1.0000
   9.500   0.9072   0.02719   0.01886  -0.0007   0.1751   1.0000
   9.750   0.9132   0.02865   0.02016   0.0018   0.1496   1.0000
  10.000   0.9211   0.03022   0.02149   0.0039   0.1289   1.0000
  10.250   0.9310   0.03175   0.02301   0.0058   0.1101   1.0000
  10.500   0.9428   0.03334   0.02455   0.0075   0.0951   1.0000
  10.750   0.9597   0.03512   0.02630   0.0086   0.0828   1.0000
  11.000   0.9805   0.03704   0.02815   0.0091   0.0728   1.0000
  11.250   0.9944   0.03870   0.02988   0.0104   0.0647   1.0000
  11.500   1.0168   0.04114   0.03254   0.0108   0.0581   1.0000
  11.750   1.0280   0.04286   0.03430   0.0122   0.0531   1.0000
  12.000   1.0534   0.04650   0.03816   0.0120   0.0494   1.0000
  12.250   1.0555   0.04892   0.04096   0.0145   0.0472   1.0000
  12.500   1.0562   0.05130   0.04361   0.0166   0.0448   1.0000
  12.750   1.0580   0.05366   0.04612   0.0184   0.0428   1.0000
  13.000   1.0624   0.05641   0.04892   0.0195   0.0408   1.0000
  13.250   1.0590   0.06101   0.05378   0.0209   0.0399   1.0000
  13.500   1.0478   0.06476   0.05782   0.0227   0.0399   1.0000
  13.750   1.0319   0.06898   0.06233   0.0243   0.0397   1.0000
  14.000   1.0145   0.07303   0.06664   0.0254   0.0397   1.0000
  14.250   0.9932   0.07761   0.07149   0.0259   0.0397   1.0000
  14.500   0.9744   0.08164   0.07575   0.0258   0.0400   1.0000
  14.750   0.9506   0.08670   0.08106   0.0247   0.0402   1.0000
  15.000   0.9199   0.09302   0.08766   0.0221   0.0407   1.0000
  15.250   0.8120   0.11523   0.11046   0.0075   0.0469   1.0000
  15.500   0.7851   0.12655   0.12180   0.0010   0.0492   1.0000
  15.750   0.7690   0.13611   0.13135  -0.0040   0.0502   1.0000
<< Back to NREL's S834 Airfoil (s834-nr)

Polar data table (+)

Polar graphs


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