[solar.spectrum]

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 = VD/


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

[truffaldino]

The definition of Re in this case depends on your purpoces. Do you want to comute Lift, Drag, CM?

[solar.spectrum]

Originally Posted by truffaldino

The definition of Re in this case depends on your purpoces. Do you want to comute Lift, Drag, CM?

yes, I want to calculate lift and drag for different reynolds number as well as Angle of attack

[FMDenaro]

your characteristic length "D" is the one that is meaningful for your problem ... any choice of a lenght is coherent with the definition of a Reynolds number, but if you want that the Re number represents the relative magnitude between convective and diffusive fluxes of the momentum quantity for your problem, then you have to choice properly the lenght..

[truffaldino]

Originally Posted by solar.spectrum

yes, I want to calculate lift and drag for different reynolds number as well as Angle of attack

What method or sotware are you going to use?

In general, single reynolds number fits only for calculation of 2D airfoil. In your case the analysys should be more sophisticated, unless you are going to have a rough estimation.

Tell us more details.

[A.D.E]

For a 2D wing (airfoil) you can use your chord length to calculate the value of Re!! If you have a tapered 3D wing then the Re will vary at the different locations. You can however calculate an average Re based on your average chord length. A more in-depth analysis can be obtained at:


Fundamentals of Aerodynamics SI by John D. Anderson


And/or


Aerodynamics for Engineers John J. Bertin, Russell M. Cummings

[Hybrid]

You have to compute the "Mean Aerodynamic Chord" and use that as a characteristics length "D" in Reynolds number formula. The formula for MAC is:

MAC = A-(2(A-B)(0.5A+B) / (3(A+B)))

here, A : Root chord of the wing
and B: Tip chord of the wing

This equation for the straight-tapered wing.

Hope this solves your problem.

[Radwanma]

Dear Ali;

Can we use the previous equation for a Twisted blade as well?

Thanks,

[Hybrid]

Yes. You can.