Free Flight, Free Speech

With a weaker tail rotor and a little more stabilization , this model will rock. My assessment of the FDM is quite contrary, but since you're a RL pilot and I'm not, I'd assume that my emphases are in the wrong areas. But I still have the following questions: 1.) Is it realistic, when I'm on the gr...

However, in many cases you can distribute the GPL-covered software alongside your proprietary system. To do this validly, you must make sure that the free and nonfree programs communicate at arms length, that they are not combined in a way that would make them effectively a single program. And audi...

"Thus, it is not the intent of this section to claim rights or contest your rights to work written entirely by you; rather, the intent is to exercise the right to control the distribution of derivative or collective works based on the Program." You should have quoted the paragraph directl...

And you implicitly set beta = 0. Can you explain where you see this ? Thats my understanding and reasoning of the following: If you were to cross section the wing following the airstream and compare it with the cross section in the u direction we'd see that the thickness of the airfoil remains cons...

I still don't fully understand your approach. In the real world the free stream can flow over the wing from a beta angle and it will travel from the leading edge to the trailing edge at this beta angle... If you were to cross section the wing following the airstream and compare it with the cross sec...

bomber wrote:

mue wrote:That means u_hstab/w_hstab = tan(alpha - downwash_angle).

apart from it being
tan theta = o/a
tan h-stab angle = w/u

Ooops...my bad. You are right. It should read w_hstab/u_hstab = tan(alpha - downwash_angle) and w/u = tan(alpha).

Changes in beta would reduce the velocity if you only used the u-fps That I don't understand. How does changes in beta reduce the (and what) velocity? the horizontal velocity used is a vector of both U and V velocities Then the angle you compute is not aerodynamic alpha but some kind of alpha total...

To determine the angle of attack on the h-stab we need to understand the two velocities uv and w with these determines it's a simple case of Pythagoras tan Angle = O/A Better yet use the atan2 function in xml as this doesn't give infinite results which would throw the AoA out. <fcs_function name=&q...

So if you completely deleted all the pitch yaw and roll moments in their sections there'd be no pitch, yaw and rolling happening.... is that correct ? Simon No. It's all in the moment (at CG) formula: M_cg = M_aerorp + (CG - AERORP) x F_aerorp. I assume with "...completely deleted all the pitc...

m_aerorp is just the aggregate of all pitch, yaw and roll moments defined in the <aerodynamics> section.