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?

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

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

Hi:

The load distibution looks like it parabolic, since the tangential velocity of the propeller is

directy propotional to the radius or distance from the hub; and the applied thrust force and

drag is proportional to the velocity squared. 

Scan and Solve has a hydrostatic load condition but nothing that would apply a parabolic load

distribution.

If version 1.6 of Scan and Solve allows scripts to be written; maybe, a script for parabolic load distibution could be written.

Without a way to apply a uniform paraboloic load distibution along the

length of the propeller vane I would break the propeller up into sections

along its length using split lines. Then I would calculate the load at the center

of each area according to its tangential velocity, planar area and coefficient for

drag or thrust.

The smaller the area, the better my approximation would be for the actual load distibution.

A propeller blade is divided into sections and each section is analysed

according to its cross sectional shape. To be accurate on the analysis you

will have to determine the thrust coefficient for each section, and from that you can

figure out the force on respective sections.

There is alot of freeware for propller and wing design available.

I will upload some software which might help you determine

Cd and Cl for each wing  section and hence the applicable forces.

Rhino has a "Split line" command. It works great.

http://www.grc.nasa.gov/WWW/k-12/FoilSim/index.html