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S4061-096-84 (s4061-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S4061-096-84 (s4061-il)
Reynolds number: 50,000
Max Cl/Cd: 39.08 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4061-il-50000-n5.txt
Download as CSV file: xf-s4061-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4061-096-84                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3392   0.09589   0.08927  -0.0414   1.0000   0.0493
  -8.250  -0.3381   0.09282   0.08629  -0.0418   1.0000   0.0491
  -8.000  -0.3377   0.09004   0.08361  -0.0414   1.0000   0.0487
  -7.750  -0.3443   0.08764   0.08134  -0.0407   1.0000   0.0485
  -7.500  -0.3534   0.08566   0.07950  -0.0393   1.0000   0.0482
  -7.250  -0.3634   0.08361   0.07756  -0.0380   1.0000   0.0478
  -7.000  -0.3744   0.08149   0.07555  -0.0369   1.0000   0.0475
  -6.750  -0.3847   0.07910   0.07323  -0.0362   1.0000   0.0472
  -6.500  -0.3924   0.07653   0.07072  -0.0359   1.0000   0.0467
  -6.250  -0.3827   0.07170   0.06586  -0.0410   0.9948   0.0463
  -6.000  -0.3588   0.06520   0.05922  -0.0495   0.9856   0.0456
  -5.750  -0.3345   0.05857   0.05235  -0.0574   0.9766   0.0448
  -5.500  -0.3075   0.05200   0.04539  -0.0647   0.9683   0.0442
  -5.250  -0.2772   0.04598   0.03882  -0.0709   0.9610   0.0441
  -5.000  -0.2477   0.04104   0.03325  -0.0750   0.9535   0.0446
  -4.750  -0.2136   0.03685   0.02833  -0.0786   0.9473   0.0464
  -4.500  -0.1810   0.03364   0.02433  -0.0807   0.9408   0.0498
  -4.250  -0.1489   0.03187   0.02236  -0.0824   0.9343   0.0543
  -4.000  -0.1123   0.02967   0.01956  -0.0842   0.9292   0.0597
  -3.750  -0.0832   0.02843   0.01819  -0.0848   0.9215   0.0691
  -3.500  -0.0456   0.02706   0.01657  -0.0867   0.9166   0.0875
  -3.250  -0.0171   0.02621   0.01565  -0.0871   0.9087   0.1143
  -3.000   0.0172   0.02536   0.01482  -0.0885   0.9028   0.1507
  -2.750   0.0466   0.02475   0.01416  -0.0890   0.8952   0.1909
  -2.500   0.0794   0.02416   0.01364  -0.0901   0.8886   0.2390
  -2.250   0.1082   0.02370   0.01326  -0.0904   0.8811   0.2940
  -2.000   0.1382   0.02321   0.01298  -0.0910   0.8741   0.3646
  -1.750   0.1648   0.02273   0.01282  -0.0907   0.8666   0.4574
  -1.500   0.1884   0.02215   0.01274  -0.0894   0.8592   0.5917
  -1.250   0.2307   0.02114   0.01240  -0.0902   0.8543   1.0000
  -1.000   0.2568   0.02141   0.01229  -0.0902   0.8450   1.0000
  -0.750   0.2870   0.02162   0.01215  -0.0907   0.8376   1.0000
  -0.500   0.3144   0.02186   0.01213  -0.0907   0.8290   1.0000
  -0.250   0.3419   0.02212   0.01215  -0.0907   0.8208   1.0000
   0.000   0.3706   0.02235   0.01215  -0.0909   0.8129   1.0000
   0.250   0.3958   0.02266   0.01229  -0.0905   0.8040   1.0000
   0.500   0.4259   0.02284   0.01230  -0.0907   0.7968   1.0000
   0.750   0.4493   0.02320   0.01254  -0.0901   0.7871   1.0000
   1.000   0.4806   0.02333   0.01254  -0.0904   0.7806   1.0000
   1.250   0.5028   0.02374   0.01287  -0.0897   0.7702   1.0000
   1.500   0.5322   0.02391   0.01295  -0.0897   0.7631   1.0000
   1.750   0.5563   0.02426   0.01325  -0.0891   0.7533   1.0000
   2.000   0.5811   0.02459   0.01353  -0.0885   0.7441   1.0000
   2.250   0.6101   0.02473   0.01363  -0.0884   0.7364   1.0000
   2.500   0.6328   0.02514   0.01404  -0.0876   0.7257   1.0000
   2.750   0.6616   0.02526   0.01415  -0.0873   0.7179   1.0000
   3.000   0.6862   0.02556   0.01446  -0.0867   0.7076   1.0000
   3.250   0.7097   0.02590   0.01483  -0.0859   0.6967   1.0000
   3.500   0.7390   0.02592   0.01489  -0.0855   0.6882   1.0000
   3.750   0.7638   0.02613   0.01515  -0.0847   0.6771   1.0000
   4.000   0.7873   0.02642   0.01549  -0.0838   0.6649   1.0000
   4.250   0.8123   0.02658   0.01575  -0.0829   0.6533   1.0000
   4.500   0.8397   0.02657   0.01581  -0.0822   0.6423   1.0000
   4.750   0.8676   0.02651   0.01582  -0.0814   0.6309   1.0000
   5.000   0.8913   0.02670   0.01610  -0.0804   0.6172   1.0000
   5.250   0.9154   0.02684   0.01638  -0.0793   0.6031   1.0000
   5.500   0.9398   0.02694   0.01658  -0.0782   0.5886   1.0000
   5.750   0.9644   0.02701   0.01676  -0.0771   0.5734   1.0000
   6.000   0.9892   0.02705   0.01694  -0.0760   0.5576   1.0000
   6.250   1.0133   0.02713   0.01712  -0.0747   0.5405   1.0000
   6.500   1.0337   0.02745   0.01759  -0.0733   0.5209   1.0000
   6.750   1.0562   0.02761   0.01785  -0.0719   0.5009   1.0000
   7.000   1.0783   0.02780   0.01815  -0.0705   0.4796   1.0000
   7.250   1.0981   0.02815   0.01860  -0.0689   0.4562   1.0000
   7.500   1.1170   0.02858   0.01910  -0.0673   0.4313   1.0000
   7.750   1.1354   0.02906   0.01960  -0.0655   0.4057   1.0000
   8.000   1.1520   0.02969   0.02026  -0.0637   0.3793   1.0000
   8.250   1.1659   0.03054   0.02113  -0.0618   0.3521   1.0000
   8.500   1.1783   0.03152   0.02210  -0.0598   0.3257   1.0000
   8.750   1.1893   0.03262   0.02318  -0.0578   0.3005   1.0000
   9.000   1.1984   0.03385   0.02435  -0.0556   0.2772   1.0000
   9.250   1.2047   0.03524   0.02575  -0.0534   0.2549   1.0000
   9.500   1.2101   0.03674   0.02724  -0.0511   0.2347   1.0000
   9.750   1.2146   0.03842   0.02894  -0.0491   0.2152   1.0000
  10.000   1.2188   0.04024   0.03079  -0.0473   0.1969   1.0000
  10.250   1.2219   0.04219   0.03276  -0.0456   0.1800   1.0000
  10.500   1.2247   0.04429   0.03488  -0.0441   0.1645   1.0000
  10.750   1.2266   0.04655   0.03716  -0.0428   0.1500   1.0000
  11.000   1.2282   0.04896   0.03962  -0.0416   0.1364   1.0000
  11.250   1.2287   0.05157   0.04232  -0.0406   0.1236   1.0000
  11.500   1.2283   0.05438   0.04521  -0.0398   0.1117   1.0000
  11.750   1.2267   0.05739   0.04831  -0.0392   0.1009   1.0000
  12.000   1.2242   0.06059   0.05157  -0.0389   0.0914   1.0000
  12.250   1.2208   0.06389   0.05483  -0.0388   0.0838   1.0000
  12.500   1.2193   0.06743   0.05862  -0.0387   0.0759   1.0000
  12.750   1.2166   0.07100   0.06220  -0.0389   0.0702   1.0000
  13.000   1.2146   0.07482   0.06628  -0.0391   0.0647   1.0000
  13.250   1.2128   0.07835   0.06976  -0.0394   0.0607   1.0000
  13.500   1.2094   0.08282   0.07458  -0.0400   0.0570   1.0000
  13.750   1.2058   0.08725   0.07924  -0.0407   0.0542   1.0000
  14.000   1.2030   0.09146   0.08358  -0.0416   0.0520   1.0000
  14.250   1.2027   0.09534   0.08751  -0.0423   0.0499   1.0000
  14.500   1.1902   0.10177   0.09430  -0.0448   0.0488   1.0000
  14.750   1.1758   0.10881   0.10164  -0.0480   0.0481   1.0000
  15.000   1.1587   0.11680   0.10990  -0.0522   0.0477   1.0000
  15.250   1.1385   0.12603   0.11934  -0.0575   0.0478   1.0000
  15.500   1.1160   0.13664   0.13014  -0.0638   0.0482   1.0000
  15.750   1.0917   0.14881   0.14241  -0.0712   0.0488   1.0000
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