Recent content by Rope

Sorry for the delay... what's MOI? If it's the moment of inertia, then the answer is no (you could nevertheless approximate it as a beam (2D) or a plate (3D).

The equation was that of the aerodynamic moment (it was rather a definition for the moment coefficient, not an equation...). Given your sketch though, that's not what you need. Assuming that you want to dimension the servo, you'd probably need the pressure distribution on the flap itself when...

I'm not sure what your geometry is (a sketch wouldn't hurt). With a wing fixed to the stand, you'll only have pitch moments to control, in which case, M=1/2 * \rho * V^2 * A * chord * Cm If you're trying to control just the flap, that's another story.

Fluids are more complicated, since they can also transport heat via convection (if they flow). Coming back to original question, heat capacity doesn't play a role in heat conduction, but rather in heat storage.

Heat conduction reflects how uniform the temperature is within a body, which is controlled by thermal conductivity. Heat capacity is defined as the ratio of input heat to variation in temperature, and reflects a body's capacity for storing heat.

Strictly speaking, Young's modulus of elasticity is tan(alpha), where alpha is the slope of the tangent line to the stress-strain curve at origin. If you define a function E_t=sigma/eps along the curve, you get the "tangent modulus, which as you noted, becomes function of total strain.

It will definitely be interesting, but the controllability will depend both on your controller design and on the stall characteristics of your airfoil (and by that I mean the hysteresis loop at large angle of attack (AOA). Appendix IV has plots of the lift, drag, and pitch moment with the...

Blue book with the airfoil on the cover... Theory of Wing Sections: Including a Summary of Airfoil Data by Ira H. Abbott, A. E. von Doenhoff Also, don't get above the stall angle, or otherwise your controller may not be able to stabilize the motion.

I guess that continuity should be du_i/dx_i=0 instead of div(u_3)=0. Anyhew, your solution seems correct up till and including the principal directions (with the note that u=u(y) only, i.e. 2-D shear flow). When I calculate the principal values and directions in the old fashion way (as...

No fully developed external flow The boundary layer thickness generally grows in the direction of the flow, and the flat plate is no exception. Thus, the velocity profile in the boundary layer will change streamwise; it is just this chage is much smaller than in the direction normal to the...

Yes. Only variable here is the Reynolds' number. Incompressible flow means rho=const, which is a good approximation for Mach<0.3~0.4. If incompressibility is waived as a simplification, you may have subsonic, etc. Note that the supersonic/subsonic is generally defined locally, or for areas of...