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SG6042 (sg6042-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SG6042 (sg6042-il)
Reynolds number: 50,000
Max Cl/Cd: 39.47 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sg6042-il-50000-n5.txt
Download as CSV file: xf-sg6042-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6042                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3689   0.10477   0.09815  -0.0324   1.0000   0.1078
  -7.750  -0.4011   0.10497   0.09855  -0.0317   1.0000   0.1116
  -7.500  -0.4202   0.10358   0.09730  -0.0308   1.0000   0.1119
  -7.250  -0.4055   0.09546   0.08908  -0.0301   1.0000   0.0650
  -7.000  -0.4282   0.09079   0.08449  -0.0348   1.0000   0.0561
  -6.750  -0.4283   0.08814   0.08190  -0.0327   1.0000   0.0550
  -6.500  -0.4317   0.08488   0.07868  -0.0327   1.0000   0.0543
  -6.250  -0.4335   0.08156   0.07539  -0.0331   1.0000   0.0534
  -6.000  -0.4341   0.07777   0.07160  -0.0345   1.0000   0.0530
  -5.750  -0.4321   0.07369   0.06748  -0.0362   1.0000   0.0526
  -5.500  -0.4267   0.06953   0.06323  -0.0381   1.0000   0.0522
  -5.250  -0.4179   0.06516   0.05873  -0.0403   1.0000   0.0517
  -5.000  -0.3927   0.05958   0.05286  -0.0459   0.9961   0.0508
  -4.750  -0.3622   0.05388   0.04671  -0.0517   0.9916   0.0496
  -4.500  -0.3294   0.04868   0.04094  -0.0566   0.9874   0.0489
  -4.250  -0.2954   0.04455   0.03626  -0.0604   0.9838   0.0491
  -4.000  -0.2633   0.04151   0.03272  -0.0630   0.9794   0.0516
  -3.750  -0.2278   0.03855   0.02909  -0.0657   0.9757   0.0543
  -3.500  -0.1910   0.03594   0.02578  -0.0679   0.9725   0.0559
  -3.250  -0.1603   0.03393   0.02340  -0.0689   0.9679   0.0579
  -3.000  -0.1281   0.03269   0.02199  -0.0702   0.9634   0.0630
  -2.750  -0.0919   0.03141   0.02021  -0.0715   0.9598   0.0690
  -2.500  -0.0648   0.03030   0.01912  -0.0716   0.9542   0.0750
  -2.250  -0.0329   0.02945   0.01809  -0.0724   0.9494   0.0862
  -2.000   0.0000   0.02875   0.01732  -0.0735   0.9448   0.1047
  -1.750   0.0295   0.02806   0.01663  -0.0741   0.9387   0.1331
  -1.500   0.0655   0.02725   0.01599  -0.0761   0.9341   0.1840
  -1.250   0.0973   0.02576   0.01566  -0.0779   0.9293   0.3897
  -1.000   0.1089   0.02478   0.01597  -0.0731   0.9226   0.7610
  -0.750   0.1439   0.02443   0.01559  -0.0736   0.9158   1.0000
  -0.500   0.1741   0.02470   0.01549  -0.0745   0.9079   1.0000
  -0.250   0.2110   0.02502   0.01545  -0.0765   0.9021   1.0000
   0.000   0.2382   0.02529   0.01548  -0.0768   0.8932   1.0000
   0.250   0.2752   0.02559   0.01552  -0.0788   0.8872   1.0000
   0.500   0.3015   0.02588   0.01563  -0.0789   0.8777   1.0000
   0.750   0.3355   0.02615   0.01571  -0.0803   0.8705   1.0000
   1.000   0.3652   0.02642   0.01585  -0.0809   0.8614   1.0000
   1.250   0.3948   0.02670   0.01601  -0.0814   0.8524   1.0000
   1.500   0.4297   0.02689   0.01610  -0.0827   0.8446   1.0000
   1.750   0.4557   0.02719   0.01632  -0.0826   0.8340   1.0000
   2.000   0.4955   0.02724   0.01631  -0.0846   0.8275   1.0000
   2.250   0.5197   0.02752   0.01656  -0.0841   0.8155   1.0000
   2.500   0.5475   0.02772   0.01674  -0.0841   0.8044   1.0000
   2.750   0.5881   0.02755   0.01658  -0.0858   0.7972   1.0000
   3.000   0.6131   0.02772   0.01676  -0.0852   0.7842   1.0000
   3.250   0.6401   0.02782   0.01689  -0.0848   0.7717   1.0000
   3.500   0.6696   0.02781   0.01691  -0.0847   0.7596   1.0000
   3.750   0.7037   0.02759   0.01677  -0.0851   0.7484   1.0000
   4.250   0.7689   0.02705   0.01638  -0.0852   0.7223   1.0000
   4.500   0.7995   0.02678   0.01622  -0.0848   0.7071   1.0000
   4.750   0.8275   0.02656   0.01609  -0.0840   0.6900   1.0000
   5.000   0.8519   0.02645   0.01607  -0.0827   0.6702   1.0000
   5.250   0.8819   0.02612   0.01585  -0.0820   0.6500   1.0000
   5.500   0.9112   0.02583   0.01564  -0.0812   0.6275   1.0000
   5.750   0.9404   0.02558   0.01544  -0.0804   0.6018   1.0000
   6.000   0.9666   0.02551   0.01541  -0.0792   0.5722   1.0000
   6.250   0.9929   0.02550   0.01537  -0.0781   0.5393   1.0000
   6.500   1.0138   0.02579   0.01560  -0.0763   0.5032   1.0000
   6.750   1.0340   0.02620   0.01589  -0.0745   0.4658   1.0000
   7.000   1.0507   0.02681   0.01640  -0.0724   0.4285   1.0000
   7.250   1.0651   0.02759   0.01703  -0.0701   0.3923   1.0000
   7.500   1.0783   0.02851   0.01780  -0.0678   0.3586   1.0000
   7.750   1.0904   0.02955   0.01870  -0.0655   0.3272   1.0000
   8.000   1.1021   0.03068   0.01975  -0.0633   0.2986   1.0000
   8.250   1.1142   0.03187   0.02087  -0.0613   0.2728   1.0000
   8.500   1.1258   0.03314   0.02202  -0.0593   0.2506   1.0000
   8.750   1.1391   0.03442   0.02330  -0.0576   0.2299   1.0000
   9.000   1.1522   0.03575   0.02464  -0.0560   0.2117   1.0000
   9.250   1.1662   0.03712   0.02600  -0.0545   0.1958   1.0000
   9.500   1.1808   0.03850   0.02742  -0.0532   0.1814   1.0000
   9.750   1.1960   0.03994   0.02891  -0.0519   0.1685   1.0000
  10.000   1.2120   0.04142   0.03046  -0.0508   0.1573   1.0000
  10.250   1.2269   0.04293   0.03198  -0.0496   0.1473   1.0000
  10.500   1.2419   0.04455   0.03380  -0.0484   0.1376   1.0000
  10.750   1.2579   0.04628   0.03568  -0.0473   0.1294   1.0000
  11.000   1.2707   0.04796   0.03741  -0.0461   0.1219   1.0000
  11.250   1.2833   0.05000   0.03972  -0.0449   0.1151   1.0000
  11.500   1.2953   0.05188   0.04172  -0.0437   0.1091   1.0000
  11.750   1.3040   0.05417   0.04424  -0.0423   0.1037   1.0000
  12.000   1.3089   0.05654   0.04687  -0.0408   0.0986   1.0000
  12.250   1.3233   0.05846   0.04872  -0.0400   0.0941   1.0000
  12.500   1.3174   0.06177   0.05252  -0.0382   0.0907   1.0000
  12.750   1.3134   0.06497   0.05603  -0.0368   0.0874   1.0000
  13.000   1.3132   0.06782   0.05906  -0.0357   0.0843   1.0000
  13.250   1.3214   0.07033   0.06157  -0.0350   0.0814   1.0000
  13.500   1.3031   0.07508   0.06676  -0.0342   0.0800   1.0000
  13.750   1.2829   0.08036   0.07241  -0.0343   0.0787   1.0000
  14.000   1.2599   0.08634   0.07871  -0.0352   0.0778   1.0000
  14.250   1.2328   0.09338   0.08604  -0.0373   0.0774   1.0000
  14.500   1.1991   0.10224   0.09514  -0.0413   0.0776   1.0000
  14.750   1.1571   0.11395   0.10705  -0.0480   0.0786   1.0000
  15.000   1.1089   0.12944   0.12264  -0.0577   0.0797   1.0000
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