AE432 - Exam 2 Part 1 Questions

Ground effect is linked to the glide ratio, L/D, of an aircraft

Yes, because of the reduction in wing tip vorticies

A pilot in an American aerobatic airplane (clockwise engine rotation) is in an upright (positive g) spin using the left rudder pedal (left spin), adding power will tend to make the spin _______________.

flat

In the 3DoF longitudinal only model, there are how many navigation states?

2

Stable airplanes roll ____________ the wind.

away from

In flight test, Vmc can be determined by _____________________.

decreasing airspeed until the rudder hits the stop

An airplane is at -180 bank, zero flight path angle, a positive angle of attack and heading 090. The direction of lift in the NED system is ____________________.

down

An airplane can be dynamically stable and statically unstable?

This definition makes little sense, so no

An accident occurs in a twin engine aircraft taking off at a short field. It is known that the right engine failed immediately after lift off. List events in order:

A) Airplane rolls inverted,

B) Pilot slows down (too much) to try and clear the trees,

C) Pilot applies rudder to maintain directional control,

D) Pilot applies full aileron,

E) Sideslip becomes large,

F) Rudder hits the stop,

G) Right engine fails

G, C, B, F, E, D, A

The following question refers to a small tailwheel (j-3) airplane in a crosswind takeoff. Neglect engine effects. The proper rudder for a crosswind situation would be _________________ rudder.

downwind

Theta dot (derivative of pitch) and q, the pitch rate __________________.

can be the same under some circumstances

This is a flight test history of the stick free motion of an airplane in pitch. The problem with this airplane is that ______________________________.

it has a problem pitch damping, Cmq

CMα is _________________________

longitudinal static stability derivative

The symbol for pitch damping is _____________ and the sign for a stable airplane is _________________.

CMq, negative

The symbol for roll damping is ______________ and ___________ is the sign for a stable airplane.

CLp, negative

Cnr is ___________________.

yaw damping

Cn∂r is ____________________________.

yaw control power

The longitudinal static stability derivative is ___________ and is ___________ for a stable airplane.

Cmα, negative

This is the stick free motion of an airplane pitch attitude. This mode is __________________.

statically stable, dynamically unstable

The following question refers to a small tailwheel (j-3) airplane in a crosswind takeoff. Neglect Engine effects. The airplane has ended up on the upwind side of centerline due to improper control usage. _________ aileron is the worst thing that a pilot could do in this situation because ___________.

downwind, dihedral effect

If a faster rise time is desired in a PID controller, the first variable to be changed would be:

P

Stable airplanes yaw ___________ the wind.

into

Stable airplanes pitch __________ the wind.

into

A positive "p" will make the left wing go _____________.

up

On a vertical up line at zero lift, an American built Pitts Special deflects the ailerons yet exhibits no rolling motion. This is because there is an opposite and equal rolling moment due to ________________.

torque

Ground effect is the compression of air under the wing of an aircraft?

false

Cn∂α is ____________________________.

adverse yaw

CL∂a is ____________________________.

roll control power

The symbol for pitch control power is ________________.

Cm∂e

The symbol for weather vane stability is ____________________ and is ______________ for stable airplanes.

Cnβ, positive

The symbol for dihedral effect is ________________ and is _____________ for stable airplane.

CLβ, negative

In the aerobatic maneuver known as an Immelman (half loop and half roll on top), left stick input requires no rudder input by the pilot to maintain heading when _____________________.

the roll is initiated on the zero lift line

The significant rudder deflection when the tail came up in the Waco video was due primarily from:

Gyroscopics

The following question refers to a small tailwheel (j-3) airplane in a crosswind takeoff. Without proper control inputs, the "wreck" will end up on the _____________ side of the runway. Neglect Engine Effects

Upwind

On the top of a humpty-bump, a pilot in an American built airplane pushes from vertical and nearly no airspeed over the top of a half loop to a vertical down. In the push substantial ____________ is required to counter act ____________.

right rudder, gyroscopics

As airplane flight on a straight vertical flight path half a wingspan from the wall of the grand canyon would experience ground effect.

no

Theta dot (derivative of pitch) and q (pitch rate) are always the same

false

Cmq is ______________.

pitch damping

The symbol for adverse yaw is ___________.

Cn∂α

CLp is ___________.

roll damping

Cm∂e is ____________.

pitch control power

If I want a faster response from a PID controller I change?

P, spring

If I want my PID system to damp faster I change?

D, damping

What is I in a PID controller?

I, Steady state error

Change of rate in heading and q, the pitch rate__________.

They can be the same in knife edge flight

The symbol for yaw control power is _______.

Cn del r

In the linearization of the 3DoF longitudinal only model using the Simulink "controls wizard" what is the size of the "A" matrix that is output?

5X5

There is a steady state error in altitude. What part of the autopilot needs tuned initially?

I

There are how many states in the longitudinal 3DoF model?

6

Ground effect is linked to the glide ration, L/D of an aircraft?

Yes, because of the reduction of wingtip vorticies

In the 3Dof longitudinal only model of the Navion, how many attitude states are there?

4

In the solving for roots, altitude ends up being ____________.

a real number close to zero

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