Physics of Flight: An Introduction by Motes Andrew

Author:Motes, Andrew [Motes, Andrew]
Language: eng
Format: epub
Publisher: AM Photonics
Published: 2016-01-10T16:00:00+00:00

C miH – this parameter relates the horizontal stabilizer angle to the pitch moment. For my simulator, this has no effect because i H = 0.

C mδe – this parameter relates elevator deflection (δ e ) to pitch moment (M ). A positive (up) elevator deflection produces a positive pitch moment, so this value will be positive. A pilot cannot control the aircraft without this. I use 0.2.

It would be nice to get values for these control derivatives from the aircraft manufacturers; otherwise, we must guess or use trial and error. I wanted to simulate a Cessna 172 but was not able to find these values documented anywhere. Luckily, I have lots of experience flying this aircraft, so I could use trial and error to make the simulator somewhat realistic; but it took some time because there are lots of variables.

Strictly speaking, these equations are only valid for straight and level flight; but for shallow climbs and dives, and slow turns, these equations should be acceptable. It is beyond the scope of this book to cover models for high-performance aircraft flight or supersonic flight.

The aerodynamic force in the AB frame’s y axis is given by

,

where C Y is the side-force coefficient and S is the wing surface area.

The moment about the AB frame’s x axis (roll axis) is given by

,

where C l is the rolling-moment coefficient and b is the wing span. It’s intuitive that a larger wingspan, wing surface area, and higher airspeed will produce larger roll moments (L ).

The moment about the AB frame’s z axis (yaw axis) is given by

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