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S4310 (s4310-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S4310 (s4310-il)
Reynolds number: 100,000
Max Cl/Cd: 58.27 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4310-il-100000-n5.txt
Download as CSV file: xf-s4310-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4310                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2788   0.09790   0.09331  -0.0400   1.0000   0.0539
  -8.500  -0.2818   0.09548   0.09098  -0.0400   1.0000   0.0545
  -8.250  -0.2908   0.09359   0.08922  -0.0389   1.0000   0.0548
  -8.000  -0.2825   0.08974   0.08540  -0.0424   0.9890   0.0543
  -7.750  -0.2682   0.08464   0.08032  -0.0486   0.9778   0.0520
  -7.250  -0.2490   0.06509   0.06063  -0.0740   0.9466   0.0280
  -7.000  -0.2335   0.06040   0.05586  -0.0790   0.9357   0.0276
  -6.750  -0.2194   0.05471   0.04999  -0.0844   0.9245   0.0272
  -6.500  -0.2059   0.04898   0.04401  -0.0888   0.9139   0.0269
  -6.250  -0.1947   0.04388   0.03856  -0.0910   0.9022   0.0267
  -6.000  -0.1810   0.03904   0.03318  -0.0925   0.8918   0.0274
  -5.750  -0.1626   0.03475   0.02816  -0.0934   0.8839   0.0286
  -5.500  -0.1441   0.03237   0.02554  -0.0932   0.8745   0.0297
  -5.250  -0.1216   0.02989   0.02265  -0.0931   0.8674   0.0303
  -5.000  -0.0990   0.02781   0.02017  -0.0926   0.8591   0.0311
  -4.750  -0.0741   0.02593   0.01790  -0.0922   0.8525   0.0322
  -4.500  -0.0493   0.02457   0.01616  -0.0917   0.8445   0.0349
  -4.250  -0.0225   0.02320   0.01439  -0.0911   0.8384   0.0371
  -4.000   0.0019   0.02189   0.01298  -0.0906   0.8305   0.0387
  -3.750   0.0286   0.02091   0.01187  -0.0901   0.8249   0.0411
  -3.500   0.0536   0.02026   0.01108  -0.0895   0.8166   0.0454
  -3.250   0.0799   0.01935   0.01006  -0.0889   0.8109   0.0486
  -3.000   0.1044   0.01874   0.00942  -0.0883   0.8028   0.0525
  -2.750   0.1310   0.01819   0.00873  -0.0877   0.7968   0.0594
  -2.500   0.1561   0.01767   0.00820  -0.0872   0.7891   0.0715
  -2.250   0.1822   0.01702   0.00763  -0.0867   0.7829   0.1003
  -2.000   0.2070   0.01642   0.00735  -0.0863   0.7756   0.1774
  -1.750   0.2316   0.01572   0.00720  -0.0859   0.7690   0.3212
  -1.500   0.2536   0.01493   0.00716  -0.0847   0.7622   0.5236
  -1.250   0.2727   0.01428   0.00715  -0.0820   0.7554   0.7255
  -1.000   0.3213   0.01384   0.00688  -0.0845   0.7503   0.9483
  -0.750   0.3646   0.01383   0.00663  -0.0877   0.7425   1.0000
  -0.500   0.3899   0.01387   0.00644  -0.0870   0.7363   1.0000
  -0.250   0.4136   0.01401   0.00643  -0.0863   0.7278   1.0000
   0.000   0.4395   0.01406   0.00628  -0.0857   0.7215   1.0000
   0.250   0.4638   0.01421   0.00631  -0.0850   0.7129   1.0000
   0.500   0.4899   0.01428   0.00622  -0.0845   0.7063   1.0000
   0.750   0.5146   0.01442   0.00626  -0.0839   0.6976   1.0000
   1.000   0.5407   0.01451   0.00623  -0.0834   0.6904   1.0000
   1.250   0.5660   0.01464   0.00626  -0.0829   0.6819   1.0000
   1.500   0.5916   0.01476   0.00629  -0.0824   0.6736   1.0000
   1.750   0.6177   0.01485   0.00629  -0.0819   0.6654   1.0000
   2.000   0.6429   0.01501   0.00639  -0.0813   0.6561   1.0000
   2.250   0.6695   0.01509   0.00637  -0.0809   0.6482   1.0000
   2.500   0.6945   0.01525   0.00652  -0.0803   0.6382   1.0000
   2.750   0.7200   0.01539   0.00662  -0.0798   0.6288   1.0000
   3.000   0.7464   0.01549   0.00664  -0.0794   0.6201   1.0000
   3.250   0.7712   0.01567   0.00683  -0.0788   0.6093   1.0000
   3.500   0.7965   0.01583   0.00698  -0.0783   0.5990   1.0000
   3.750   0.8223   0.01596   0.00706  -0.0778   0.5892   1.0000
   4.000   0.8473   0.01613   0.00723  -0.0772   0.5779   1.0000
   4.250   0.8720   0.01632   0.00743  -0.0766   0.5659   1.0000
   4.500   0.8967   0.01650   0.00764  -0.0760   0.5538   1.0000
   4.750   0.9213   0.01669   0.00782  -0.0754   0.5412   1.0000
   5.000   0.9457   0.01689   0.00802  -0.0747   0.5280   1.0000
   5.250   0.9698   0.01711   0.00826  -0.0740   0.5142   1.0000
   5.500   0.9934   0.01736   0.00851  -0.0733   0.4997   1.0000
   5.750   1.0167   0.01762   0.00878  -0.0725   0.4846   1.0000
   6.000   1.0396   0.01792   0.00908  -0.0717   0.4687   1.0000
   6.250   1.0620   0.01824   0.00943  -0.0708   0.4524   1.0000
   6.500   1.0838   0.01860   0.00978  -0.0698   0.4355   1.0000
   6.750   1.1051   0.01899   0.01016  -0.0688   0.4184   1.0000
   7.000   1.1257   0.01943   0.01058  -0.0678   0.4008   1.0000
   7.250   1.1456   0.01991   0.01110  -0.0666   0.3829   1.0000
   7.500   1.1647   0.02043   0.01162  -0.0654   0.3650   1.0000
   7.750   1.1831   0.02100   0.01217  -0.0641   0.3476   1.0000
   8.000   1.2004   0.02162   0.01277  -0.0627   0.3306   1.0000
   8.250   1.2170   0.02228   0.01343  -0.0612   0.3140   1.0000
   8.500   1.2328   0.02297   0.01416  -0.0597   0.2980   1.0000
   8.750   1.2475   0.02371   0.01492  -0.0580   0.2825   1.0000
   9.000   1.2612   0.02450   0.01571  -0.0563   0.2682   1.0000
   9.250   1.2728   0.02531   0.01654  -0.0542   0.2546   1.0000
   9.500   1.2829   0.02618   0.01744  -0.0520   0.2419   1.0000
   9.750   1.2925   0.02713   0.01844  -0.0500   0.2298   1.0000
  10.000   1.3023   0.02812   0.01950  -0.0480   0.2179   1.0000
  10.250   1.3113   0.02920   0.02064  -0.0462   0.2066   1.0000
  10.500   1.3198   0.03036   0.02186  -0.0444   0.1964   1.0000
  10.750   1.3265   0.03167   0.02317  -0.0426   0.1866   1.0000
  11.000   1.3344   0.03298   0.02460  -0.0411   0.1766   1.0000
  11.250   1.3415   0.03440   0.02610  -0.0396   0.1676   1.0000
  11.750   1.3528   0.03760   0.02949  -0.0369   0.1508   1.0000
  12.000   1.3571   0.03939   0.03134  -0.0357   0.1433   1.0000
  12.250   1.3613   0.04125   0.03332  -0.0346   0.1358   1.0000
  12.500   1.3653   0.04323   0.03538  -0.0336   0.1291   1.0000
  12.750   1.3678   0.04537   0.03764  -0.0328   0.1223   1.0000
  13.000   1.3702   0.04761   0.03997  -0.0321   0.1163   1.0000
  13.250   1.3717   0.05001   0.04250  -0.0315   0.1102   1.0000
  13.500   1.3719   0.05258   0.04515  -0.0310   0.1051   1.0000
  13.750   1.3722   0.05529   0.04804  -0.0308   0.0990   1.0000
  14.000   1.3683   0.05843   0.05118  -0.0308   0.0942   1.0000
  14.250   1.3673   0.06152   0.05455  -0.0309   0.0881   1.0000
  14.500   1.3604   0.06534   0.05842  -0.0316   0.0829   1.0000
  14.750   1.3559   0.06914   0.06241  -0.0324   0.0767   1.0000
  15.000   1.3473   0.07361   0.06697  -0.0337   0.0716   1.0000
  15.250   1.3400   0.07815   0.07166  -0.0351   0.0660   1.0000
  15.500   1.3302   0.08326   0.07688  -0.0369   0.0612   1.0000
  15.750   1.3200   0.08863   0.08237  -0.0390   0.0565   1.0000
  16.000   1.3104   0.09407   0.08798  -0.0412   0.0524   1.0000
  16.250   1.2976   0.10022   0.09422  -0.0439   0.0495   1.0000
  16.500   1.2876   0.10605   0.10019  -0.0465   0.0468   1.0000
  16.750   1.2764   0.11229   0.10662  -0.0494   0.0434   1.0000
  17.000   1.2634   0.11903   0.11347  -0.0528   0.0409   1.0000
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