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S9026 (9.5%) (s9026-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S9026 (9.5%) (s9026-il)
Reynolds number: 50,000
Max Cl/Cd: 24.18 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9026-il-50000.txt
Download as CSV file: xf-s9026-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9026 (9.5%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6904   0.08866   0.08156  -0.0017   1.0000   0.1767
  -9.000  -0.7300   0.07828   0.07130  -0.0097   1.0000   0.1620
  -8.750  -0.7836   0.06768   0.06044  -0.0155   1.0000   0.1491
  -8.500  -0.7877   0.06222   0.05478  -0.0160   1.0000   0.1484
  -8.250  -0.7910   0.05681   0.04906  -0.0160   1.0000   0.1478
  -8.000  -0.7917   0.05158   0.04338  -0.0156   1.0000   0.1479
  -7.750  -0.7901   0.04677   0.03788  -0.0147   1.0000   0.1494
  -7.500  -0.7696   0.04452   0.03577  -0.0138   1.0000   0.1589
  -7.250  -0.7605   0.04067   0.03129  -0.0126   1.0000   0.1651
  -7.000  -0.7410   0.03809   0.02856  -0.0115   1.0000   0.1741
  -6.750  -0.7228   0.03585   0.02614  -0.0103   1.0000   0.1874
  -6.500  -0.7032   0.03350   0.02356  -0.0091   1.0000   0.2006
  -6.250  -0.6835   0.03159   0.02143  -0.0079   1.0000   0.2185
  -6.000  -0.6624   0.02964   0.01931  -0.0067   1.0000   0.2369
  -5.750  -0.6406   0.02817   0.01791  -0.0054   1.0000   0.2602
  -5.500  -0.6187   0.02666   0.01641  -0.0041   1.0000   0.2860
  -5.250  -0.5973   0.02534   0.01516  -0.0027   1.0000   0.3169
  -5.000  -0.5764   0.02413   0.01402  -0.0011   1.0000   0.3532
  -4.750  -0.5559   0.02310   0.01318   0.0008   1.0000   0.3942
  -4.500  -0.5359   0.02217   0.01244   0.0028   1.0000   0.4400
  -4.250  -0.5159   0.02136   0.01190   0.0052   1.0000   0.4877
  -4.000  -0.4967   0.02069   0.01145   0.0079   1.0000   0.5393
  -3.750  -0.4777   0.02016   0.01116   0.0109   1.0000   0.5917
  -3.500  -0.4596   0.01974   0.01092   0.0142   1.0000   0.6458
  -3.250  -0.4410   0.01953   0.01087   0.0181   1.0000   0.6968
  -3.000  -0.4235   0.01937   0.01080   0.0221   1.0000   0.7491
  -2.750  -0.3997   0.01943   0.01091   0.0257   1.0000   0.7990
  -2.500  -0.3642   0.01961   0.01100   0.0270   1.0000   0.8514
  -2.250  -0.2781   0.02024   0.01128   0.0192   1.0000   0.9025
  -2.000  -0.1612   0.02019   0.01078   0.0035   1.0000   0.9501
  -1.750  -0.0572   0.01914   0.00940  -0.0121   1.0000   0.9920
  -1.500  -0.0283   0.01830   0.00850  -0.0149   1.0000   1.0000
  -1.250  -0.0199   0.01776   0.00797  -0.0136   1.0000   1.0000
  -1.000  -0.0125   0.01733   0.00755  -0.0118   1.0000   1.0000
  -0.750  -0.0066   0.01700   0.00724  -0.0095   1.0000   1.0000
  -0.500  -0.0028   0.01675   0.00703  -0.0067   1.0000   1.0000
  -0.250  -0.0008   0.01660   0.00690  -0.0035   1.0000   1.0000
   0.000   0.0000   0.01655   0.00687   0.0000   1.0000   1.0000
   0.250   0.0008   0.01660   0.00691   0.0035   1.0000   1.0000
   0.500   0.0028   0.01675   0.00703   0.0067   1.0000   1.0000
   0.750   0.0066   0.01700   0.00724   0.0095   1.0000   1.0000
   1.000   0.0125   0.01733   0.00755   0.0118   1.0000   1.0000
   1.250   0.0199   0.01776   0.00797   0.0136   1.0000   1.0000
   1.500   0.0282   0.01830   0.00850   0.0149   1.0000   1.0000
   1.750   0.0573   0.01913   0.00940   0.0121   0.9920   1.0000
   2.000   0.1614   0.02019   0.01077  -0.0035   0.9499   1.0000
   2.250   0.2784   0.02023   0.01128  -0.0193   0.9024   1.0000
   2.500   0.3642   0.01961   0.01100  -0.0270   0.8513   1.0000
   2.750   0.3998   0.01942   0.01091  -0.0257   0.7988   1.0000
   3.000   0.4236   0.01937   0.01080  -0.0222   0.7491   1.0000
   3.250   0.4411   0.01953   0.01087  -0.0181   0.6967   1.0000
   3.500   0.4598   0.01974   0.01092  -0.0143   0.6458   1.0000
   3.750   0.4778   0.02016   0.01116  -0.0109   0.5916   1.0000
   4.000   0.4968   0.02069   0.01146  -0.0079   0.5393   1.0000
   4.250   0.5160   0.02136   0.01190  -0.0052   0.4876   1.0000
   4.500   0.5360   0.02217   0.01244  -0.0028   0.4399   1.0000
   4.750   0.5559   0.02310   0.01318  -0.0008   0.3941   1.0000
   5.000   0.5765   0.02413   0.01402   0.0011   0.3532   1.0000
   5.250   0.5974   0.02534   0.01517   0.0026   0.3168   1.0000
   5.500   0.6188   0.02666   0.01641   0.0041   0.2860   1.0000
   5.750   0.6406   0.02816   0.01791   0.0054   0.2602   1.0000
   6.000   0.6624   0.02964   0.01931   0.0067   0.2369   1.0000
   6.250   0.6835   0.03159   0.02143   0.0079   0.2185   1.0000
   6.500   0.7032   0.03350   0.02356   0.0091   0.2005   1.0000
   6.750   0.7227   0.03585   0.02613   0.0103   0.1873   1.0000
   7.000   0.7410   0.03809   0.02856   0.0115   0.1741   1.0000
   7.250   0.7606   0.04066   0.03127   0.0126   0.1650   1.0000
   7.500   0.7695   0.04451   0.03577   0.0138   0.1587   1.0000
   7.750   0.7899   0.04676   0.03787   0.0147   0.1494   1.0000
   8.000   0.7915   0.05159   0.04339   0.0157   0.1479   1.0000
   8.250   0.7908   0.05681   0.04906   0.0160   0.1478   1.0000
   8.500   0.7876   0.06222   0.05477   0.0160   0.1484   1.0000
   8.750   0.7829   0.06771   0.06046   0.0155   0.1491   1.0000
   9.000   0.7305   0.07822   0.07124   0.0097   0.1620   1.0000
   9.250   0.6856   0.08945   0.08235   0.0004   0.1798   1.0000
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