10

An INS gives your speed & orientation in space, but without reference to what the airmass that you're flying in is doing. The Pitot tube and AOA sensors give speed and pitch orientation in relation to the local airmass, only. An indicated airspeed of 60 knots, measured by the Pitot tube, may correspond to a stationary aircraft pointed into 60 knots of ...


3

The question mentions Speed and Orientation which are broad terms that could include: Group1: (Air Data sensor + computation) IAS - Indicated Air Speed CAS - Calibrated Air Speed EAS - EquivalentAir Speed. TAS - True Air Speed AoA - Angle of Attack (HDG(M) - Magnetic Heading)^^ Group2a : (Inertial/Rate sensor + computation) GS - Ground Speed HDG(T) - ...


2

The question should really read, "how the pitch must change along the length to keep lift distribution reasonably constant while respecting stall considerations" or something like that. Rotor blades twist nose down going outboard, like propellers but with less twist, to account for the higher velocity toward the tip, so that the slower moving root ...


2

The answer to the title question is no, sideslip angle and drift angle are not the same thing. (in this figure, or any other...) What the diagram shows is drift angle, and drift angle only. If you are moving through a uniform airmass that is itself moving relative to the ground, your path across the ground (ground track, or course) will be affected by the ...


2

Wolfgang Langewiesche is right to appropriate order of approximation. For every elevator position a statically stable airplane settles to a specific equilibrium angle of attack. That's how static stability works. Airplane is statically stable if and only if increasing angle of attack causes higher increase in coefficient of lift on the aft airfoil (tail for ...


1

Consider a helicopter in hover, and the airspeed of the blades near the hub and at the tips. Also consider that downwash is being produced through the rotor disc, so the blades must be inclined somewhat to maintain a positive AoA.


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