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S8064 (s8064-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S8064 (s8064-il)
Reynolds number: 50,000
Max Cl/Cd: 29.31 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s8064-il-50000-n5.txt
Download as CSV file: xf-s8064-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8064                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5236   0.09577   0.08870  -0.0525   1.0000   0.0392
 -11.250  -0.5326   0.08984   0.08281  -0.0557   1.0000   0.0389
 -11.000  -0.5443   0.08416   0.07714  -0.0589   1.0000   0.0386
 -10.750  -0.5613   0.07860   0.07158  -0.0619   1.0000   0.0382
 -10.500  -0.5809   0.07385   0.06680  -0.0637   1.0000   0.0379
 -10.250  -0.5999   0.07016   0.06308  -0.0638   1.0000   0.0375
 -10.000  -0.6258   0.06710   0.05995  -0.0619   1.0000   0.0375
  -9.750  -0.6478   0.06510   0.05793  -0.0583   1.0000   0.0369
  -9.500  -0.6748   0.06335   0.05611  -0.0531   1.0000   0.0370
  -9.250  -0.6963   0.06115   0.05377  -0.0485   1.0000   0.0370
  -9.000  -0.7132   0.05888   0.05133  -0.0442   1.0000   0.0369
  -8.750  -0.7285   0.05633   0.04852  -0.0398   1.0000   0.0373
  -8.500  -0.7379   0.05374   0.04565  -0.0359   1.0000   0.0374
  -8.250  -0.7448   0.05091   0.04243  -0.0320   1.0000   0.0380
  -8.000  -0.7460   0.04818   0.03931  -0.0286   1.0000   0.0384
  -7.750  -0.7431   0.04542   0.03609  -0.0254   1.0000   0.0390
  -7.500  -0.7357   0.04280   0.03317  -0.0228   1.0000   0.0399
  -7.250  -0.7258   0.04078   0.03102  -0.0207   1.0000   0.0418
  -7.000  -0.7142   0.03904   0.02906  -0.0185   1.0000   0.0448
  -6.750  -0.6993   0.03715   0.02672  -0.0164   1.0000   0.0489
  -6.500  -0.6835   0.03533   0.02480  -0.0147   1.0000   0.0530
  -6.250  -0.6672   0.03393   0.02319  -0.0129   1.0000   0.0600
  -6.000  -0.6510   0.03247   0.02171  -0.0111   1.0000   0.0684
  -5.750  -0.6344   0.03119   0.02033  -0.0092   1.0000   0.0796
  -5.500  -0.6188   0.02998   0.01908  -0.0073   1.0000   0.0952
  -5.250  -0.6033   0.02883   0.01784  -0.0054   1.0000   0.1142
  -5.000  -0.5892   0.02765   0.01676  -0.0035   1.0000   0.1385
  -4.750  -0.5750   0.02649   0.01572  -0.0017   1.0000   0.1731
  -4.500  -0.5621   0.02518   0.01479   0.0002   1.0000   0.2274
  -4.250  -0.5508   0.02378   0.01401   0.0022   1.0000   0.3245
  -4.000  -0.5337   0.02275   0.01386   0.0040   0.9961   0.4848
  -3.750  -0.5122   0.02272   0.01431   0.0064   0.9920   0.6117
  -3.500  -0.4880   0.02320   0.01482   0.0085   0.9874   0.6935
  -3.250  -0.4630   0.02370   0.01514   0.0100   0.9828   0.7501
  -3.000  -0.4387   0.02415   0.01541   0.0117   0.9779   0.7925
  -2.750  -0.4068   0.02476   0.01580   0.0122   0.9739   0.8283
  -2.500  -0.3683   0.02539   0.01619   0.0113   0.9707   0.8600
  -2.250  -0.3270   0.02586   0.01639   0.0093   0.9671   0.8859
  -2.000  -0.2772   0.02630   0.01656   0.0052   0.9642   0.9048
  -1.750  -0.2264   0.02664   0.01664   0.0003   0.9612   0.9195
  -1.500  -0.1733   0.02693   0.01668  -0.0053   0.9585   0.9313
  -1.250  -0.1291   0.02706   0.01663  -0.0093   0.9541   0.9432
  -1.000  -0.0808   0.02721   0.01660  -0.0143   0.9500   0.9531
  -0.750  -0.0312   0.02738   0.01663  -0.0195   0.9462   0.9623
  -0.500   0.0122   0.02751   0.01666  -0.0237   0.9414   0.9723
  -0.250   0.0561   0.02760   0.01666  -0.0280   0.9361   0.9815
   0.000   0.1046   0.02773   0.01674  -0.0332   0.9318   0.9896
   0.250   0.1472   0.02783   0.01680  -0.0374   0.9262   0.9986
   0.500   0.1754   0.02795   0.01690  -0.0387   0.9188   1.0000
   0.750   0.1939   0.02807   0.01702  -0.0381   0.9098   1.0000
   1.000   0.2232   0.02823   0.01720  -0.0394   0.9028   1.0000
   1.250   0.2366   0.02836   0.01734  -0.0377   0.8923   1.0000
   1.500   0.2583   0.02853   0.01753  -0.0375   0.8837   1.0000
   1.750   0.2814   0.02869   0.01773  -0.0374   0.8749   1.0000
   2.000   0.2941   0.02885   0.01792  -0.0354   0.8640   1.0000
   2.250   0.3161   0.02901   0.01815  -0.0349   0.8548   1.0000
   2.500   0.3394   0.02916   0.01836  -0.0347   0.8454   1.0000
   2.750   0.3517   0.02931   0.01856  -0.0324   0.8335   1.0000
   3.000   0.3688   0.02945   0.01877  -0.0309   0.8223   1.0000
   3.250   0.4052   0.02949   0.01896  -0.0325   0.8143   1.0000
   3.500   0.4190   0.02959   0.01912  -0.0303   0.8012   1.0000
   3.750   0.4360   0.02964   0.01927  -0.0285   0.7881   1.0000
   4.000   0.4555   0.02965   0.01941  -0.0270   0.7747   1.0000
   4.250   0.4777   0.02958   0.01947  -0.0258   0.7611   1.0000
   4.500   0.5028   0.02937   0.01942  -0.0249   0.7468   1.0000
   4.750   0.5311   0.02899   0.01922  -0.0242   0.7318   1.0000
   5.000   0.5641   0.02826   0.01874  -0.0237   0.7158   1.0000
   5.250   0.5838   0.02777   0.01842  -0.0213   0.6949   1.0000
   5.500   0.6183   0.02662   0.01751  -0.0203   0.6723   1.0000
   5.750   0.6443   0.02575   0.01684  -0.0181   0.6422   1.0000
   6.000   0.6630   0.02524   0.01645  -0.0152   0.6037   1.0000
   6.250   0.6893   0.02459   0.01583  -0.0130   0.5503   1.0000
   6.500   0.7134   0.02434   0.01537  -0.0107   0.4721   1.0000
   6.750   0.7254   0.02489   0.01543  -0.0073   0.3802   1.0000
   7.000   0.7274   0.02605   0.01605  -0.0033   0.3050   1.0000
   7.250   0.7289   0.02746   0.01703   0.0003   0.2452   1.0000
   7.500   0.7336   0.02895   0.01817   0.0031   0.2014   1.0000
   7.750   0.7421   0.03041   0.01943   0.0054   0.1697   1.0000
   8.000   0.7530   0.03188   0.02073   0.0073   0.1471   1.0000
   8.250   0.7679   0.03325   0.02210   0.0087   0.1281   1.0000
   8.500   0.7872   0.03466   0.02353   0.0098   0.1136   1.0000
   8.750   0.8092   0.03608   0.02501   0.0104   0.1000   1.0000
   9.000   0.8388   0.03774   0.02672   0.0103   0.0892   1.0000
   9.250   0.8631   0.03943   0.02849   0.0106   0.0791   1.0000
   9.500   0.8911   0.04156   0.03100   0.0105   0.0703   1.0000
   9.750   0.9127   0.04376   0.03326   0.0108   0.0638   1.0000
  10.000   0.9275   0.04607   0.03597   0.0122   0.0581   1.0000
  10.250   0.9407   0.04817   0.03810   0.0132   0.0540   1.0000
  10.500   0.9488   0.05119   0.04155   0.0151   0.0513   1.0000
  10.750   0.9490   0.05412   0.04490   0.0175   0.0489   1.0000
  11.000   0.9468   0.05680   0.04787   0.0198   0.0468   1.0000
  11.250   0.9437   0.05950   0.05078   0.0218   0.0450   1.0000
  11.500   0.9391   0.06245   0.05393   0.0235   0.0440   1.0000
  11.750   0.9322   0.06574   0.05741   0.0250   0.0432   1.0000
  12.000   0.9223   0.06940   0.06126   0.0261   0.0427   1.0000
  12.250   0.9084   0.07344   0.06550   0.0268   0.0425   1.0000
  12.750   0.8669   0.08329   0.07580   0.0257   0.0425   1.0000
  13.000   0.8333   0.09062   0.08338   0.0224   0.0431   1.0000
  13.250   0.7701   0.10621   0.09920   0.0119   0.0463   1.0000
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