Announcing Scan&Solve™ for Rhino: Stress Analysis Made Easy

Comment

Comment by Karl Witt on April 27, 2012 at 1:59pm

Thanks; i already know the spanwise loading, which scales with the local airfoil chord on an elliptical planform wing. A uniform load overestimates the bend moment at the root. I would like to scale the local load to the local chord or surface area.

Comment by Bob Johansson on April 27, 2012 at 11:16am

This is the drag on an immersed body. F = (CD) * (1/2 * rho * V^2*A).

Comment by Bob Johansson on April 27, 2012 at 10:29am

HI:

 

I think the answer to the pressure distribution is it depends on what you are trying to accomplish.

Designers often simplify things to accomplish their work. A simple linear pressure distribution,

if the magnitude was correct, would allow a designer to determine if a propeller was strong enough to

do its job. He would be treating the propeller blades as a cantilever.

 

If you wanted to determine what the pressure ditribution actually looked like I beleive you would need

to use computational fluid dynamics or do physical testing and take meaurements. The are handbooks

with standard airfoils and hydrofoils avaiable which provide the pressure distribution for the standard

cross sections.

 

Thx,

 

Bob

 

Comment by Karl Witt on April 27, 2012 at 6:49am

That load distribution probably works for a propeller as the tips move faster than the root, but how would I apply a pressure to one side of the propeller only, as would be appropriate for a simple wing?

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