GUS gouge Flashcards
(43 cards)
The design of a jet intake should accelerate the air to between
0.4M and 0.7M
For aircraft operating beyond approx M1.5, multiple shock intakes are used because
the flow is decelerated through a series of oblique shcokwaves resulting in less pressure loses
the purpose of a sharp lip on a supersonic pitot intake is to
lower the speed at which the normal shockwave attaches
the immediate effects of an engine failure in a multi engine aircraft is yaw and roll to the live engine??
FALSE
the critical engine is the engine which, when failed, gives the greatest yaw??
TRUE
what is Vmca?
min speed for maintaining control of aeroplane with critical engine inoperative and maintain straight flight with an AoB not more than 5 degrees
to overcome increased control forces at high speeds a typical flight control system would use?
powered controls
spoilers are often fitted instead of ailerons because
on long thin wings ailerons can cause twisting and possible control reversal
what is “q” feel
artificial feel control system where stick force is proportional to dynamic pressure
purpose of area ruling is to
reduce wave drag
3 techniques used in applying the area rule
- waisting the fuselage
- combining a flat sided fuselage with highly swept wings
- fitting pods on trailing edge
a multiple shock intake has greater Q losses but smoother deceleration than a single shock intake because flow passes through numerous shockwaves?
FALSE
3 advantages of swept wings
- increased Mcrit and Mcdr
- reduced wave drag
- decreased thickness to chord ratio
in supersonic flight, more “subsonic” aerofoil section can be used at the tips of a swept wing because
of flow deceleration caused by inboard shockwaves
the purpose of variable geometry wings is to
improve efficiency of wing through a broader range of speeds (who knew ayy)
the main advantage of a canard is
contributes to lift produced by main wing
what flight regime can LOCAL mach numbers be greater or less than 1.0
transonic
the speed of sound in air is a function of
temperature
if increasing altitude at a constant IAS, what happens to TAS and Mach Number?
TAS increases and Mach No increases
the formation of a bow wave is dependent on the shape of the leading edge and the speed of the object?
TRUE
when SUPERsonic flow passes through a divergent duct, what happens to velocity, density and pressure?
velocity increases whilst pressure and density decrease
when SUBsonic flow passes through a convergent duct, what happens to pressure and velocity
velocity increases and pressure decreases
supersonic flow around a compressive corner will do what WRT pressure and velocity
decelerate and increase pressure
expansion fans form at a compressive corner?
FALSE
