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S6063 7.05% (s6063-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S6063 7.05% (s6063-il)
Reynolds number: 50,000
Max Cl/Cd: 34.71 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s6063-il-50000.txt
Download as CSV file: xf-s6063-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S6063 7.05%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.5196   0.09618   0.08961   0.0068   1.0000   0.2578
  -7.500  -0.5206   0.09322   0.08674   0.0062   1.0000   0.2700
  -7.250  -0.5206   0.09025   0.08386   0.0060   1.0000   0.2833
  -6.750  -0.5062   0.08328   0.07699   0.0073   1.0000   0.3139
  -6.500  -0.5001   0.08003   0.07380   0.0080   1.0000   0.3313
  -6.250  -0.5044   0.07748   0.07137   0.0073   1.0000   0.3528
  -6.000  -0.4894   0.07361   0.06751   0.0092   1.0000   0.3708
  -5.750  -0.4845   0.07064   0.06462   0.0105   1.0000   0.3969
  -5.500  -0.4653   0.05045   0.04278  -0.0351   1.0000   0.1283
  -5.250  -0.4443   0.04502   0.03706  -0.0356   1.0000   0.1128
  -5.000  -0.4217   0.04037   0.03145  -0.0362   1.0000   0.1009
  -4.750  -0.4003   0.03656   0.02750  -0.0357   1.0000   0.0982
  -4.500  -0.3773   0.03338   0.02382  -0.0352   1.0000   0.0975
  -4.250  -0.3530   0.03070   0.02057  -0.0344   1.0000   0.0996
  -4.000  -0.3288   0.02808   0.01760  -0.0335   1.0000   0.1031
  -3.750  -0.3039   0.02585   0.01514  -0.0324   1.0000   0.1079
  -3.500  -0.2781   0.02380   0.01279  -0.0310   1.0000   0.1159
  -3.250  -0.2540   0.02199   0.01104  -0.0296   1.0000   0.1398
  -3.000  -0.2308   0.01950   0.00921  -0.0284   1.0000   0.2400
  -2.750  -0.1430   0.01527   0.00759  -0.0313   1.0000   1.0000
  -2.500  -0.1349   0.01496   0.00691  -0.0292   1.0000   1.0000
  -2.250  -0.1229   0.01480   0.00640  -0.0272   1.0000   1.0000
  -2.000  -0.1081   0.01472   0.00597  -0.0255   1.0000   1.0000
  -1.750  -0.0914   0.01469   0.00563  -0.0240   1.0000   1.0000
  -1.500  -0.0736   0.01469   0.00535  -0.0227   1.0000   1.0000
  -1.250  -0.0550   0.01473   0.00510  -0.0215   1.0000   1.0000
  -1.000  -0.0358   0.01480   0.00494  -0.0204   1.0000   1.0000
  -0.750  -0.0164   0.01490   0.00485  -0.0194   1.0000   1.0000
  -0.500   0.0034   0.01503   0.00481  -0.0185   1.0000   1.0000
  -0.250   0.0232   0.01520   0.00483  -0.0177   1.0000   1.0000
   0.000   0.0430   0.01539   0.00488  -0.0169   1.0000   1.0000
   0.250   0.0628   0.01562   0.00500  -0.0162   1.0000   1.0000
   0.500   0.0825   0.01589   0.00519  -0.0155   1.0000   1.0000
   0.750   0.1019   0.01621   0.00544  -0.0149   1.0000   1.0000
   1.000   0.1211   0.01656   0.00576  -0.0144   1.0000   1.0000
   1.250   0.1399   0.01698   0.00614  -0.0140   1.0000   1.0000
   1.500   0.1583   0.01745   0.00661  -0.0136   1.0000   1.0000
   1.750   0.1763   0.01798   0.00716  -0.0134   1.0000   1.0000
   2.000   0.1937   0.01860   0.00780  -0.0132   1.0000   1.0000
   2.250   0.2105   0.01929   0.00853  -0.0132   1.0000   1.0000
   2.500   0.2383   0.02024   0.00959  -0.0154   0.9947   1.0000
   2.750   0.3091   0.02159   0.01118  -0.0253   0.9657   1.0000
   3.000   0.3779   0.02260   0.01250  -0.0340   0.9344   1.0000
   3.250   0.4536   0.02316   0.01354  -0.0428   0.9015   1.0000
   3.500   0.5146   0.02326   0.01407  -0.0477   0.8649   1.0000
   3.750   0.5700   0.02293   0.01423  -0.0502   0.8275   1.0000
   4.000   0.6124   0.02235   0.01401  -0.0493   0.7884   1.0000
   4.250   0.6417   0.02185   0.01377  -0.0460   0.7452   1.0000
   4.500   0.6657   0.02138   0.01349  -0.0417   0.6969   1.0000
   4.750   0.6870   0.02100   0.01325  -0.0370   0.6413   1.0000
   5.000   0.7044   0.02068   0.01283  -0.0316   0.5688   1.0000
   5.250   0.7126   0.02053   0.01216  -0.0254   0.4516   1.0000
   5.500   0.7124   0.02296   0.01291  -0.0203   0.2250   1.0000
   5.750   0.7280   0.02651   0.01548  -0.0182   0.1303   1.0000
   6.000   0.7535   0.02912   0.01782  -0.0169   0.1101   1.0000
   6.250   0.7823   0.03160   0.02060  -0.0158   0.1009   1.0000
   6.500   0.8094   0.03468   0.02384  -0.0150   0.0958   1.0000
   6.750   0.8334   0.03759   0.02733  -0.0139   0.0914   1.0000
   7.000   0.8553   0.04062   0.03068  -0.0130   0.0874   1.0000
   7.250   0.8749   0.04434   0.03487  -0.0120   0.0866   1.0000
   7.500   0.8885   0.04888   0.04021  -0.0108   0.0889   1.0000
   7.750   0.8979   0.05391   0.04584  -0.0100   0.0919   1.0000
   8.000   0.9060   0.05897   0.05129  -0.0094   0.0949   1.0000
   8.250   0.9120   0.06411   0.05683  -0.0091   0.0988   1.0000
   8.500   0.8932   0.07099   0.06429  -0.0104   0.1053   1.0000
   8.750   0.8983   0.07665   0.07007  -0.0108   0.1117   1.0000
   9.000   0.8564   0.08391   0.07755  -0.0155   0.1167   1.0000
   9.250   0.8450   0.09074   0.08440  -0.0189   0.1260   1.0000
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