Calculate Reynolds Number for NACA 4412 Wing

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SUMMARY

The discussion focuses on calculating the Reynolds number for a NACA 4412 wing design. The formula for Reynolds number is given as Re = ρVD/μ, where ρ is the air density (0.65970 kg/m³), V is the freestream velocity (100 m/s), D is the characteristic length (typically the mean aerodynamic chord), and μ is the dynamic viscosity (0.00001594 N·s/m²). The mean aerodynamic chord is recommended for this calculation, although other chord lengths can be used based on specific interests. Additional parameters include a wing taper ratio of 0.3, a sweep angle of 37 degrees, and an altitude of 6000m.

PREREQUISITES
  • Understanding of fluid dynamics principles
  • Familiarity with the Reynolds number concept
  • Knowledge of aerodynamic properties of airfoils
  • Basic proficiency in using NACA airfoil data
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Aerospace engineers, aerodynamicists, and students studying fluid dynamics or aircraft design will benefit from this discussion.

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hey guys, I would like to know about reynold's number for a wing

I have designed a NACA 4412 wing which has wingroot = a , wingtip = b and winglet tip = c (a,b,c are any integers or decimals)

please tell me the formula of calculating D for the eqn of reynolds number = ρVD/μ


additional info : Wing taper ratio = 0.3 , sweep and sweepback angle = 37 degree

altitude = 6000m , density = 0.65970 kg/m3, Pressure = 47182.5 Pa ,
Temp= 249.2K , velocity of freestream= 100m/s, viscosity= 0.00001594 N sec/m^2
 
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For a wing the length scale for the Reynolds number is typically the mean aerodynamic chord of the wing.

http://en.wikipedia.org/wiki/Chord_(aircraft)#Mean_aerodynamic_chord

however you can also use the root chord or the tip chord or any thing in between really. The choice depends on what you are interested in. However the convention for a wing is the mean aerodynamic chord so I am assuming that is probably what you want.
 

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