Forward Flight

Question 1

During straight and level flight the two components of total rotor thrust are the forward ——- component to overcome (weight/parasite drag) and the ——- component to overcome (weight, parasite drag)

Answer 1

Thrust
Parasite drag
Vertical
Weight

Question 2

In stabilised straight and level flight, the fuselage attitude is determined by the resultant of ——- and ——- passing through the centre of (pressure, gravity) of the aircraft.

Answer 2

Weight
Drag
Gravity

Question 3

When moving cyclic forward, the pitch angle is (greatest, smallest) on the advancing side of the disc and angles of attack, as a direct result of cyclic, (do, do not) change.

Answer 3

Smallest
Do not

Question 4

When moving cyclic to the right in a helicopter with a clockwise rotating rotor, the pitch angle is greatest when the pitch angle is over the (nose, tail, left, right) of the aircraft.

Answer 4

Tail

Question 5

Dissymetry of lift is caused by ——- airspeed affecting the advancing blade and ——- airspeed affecting the ——- blade.

Answer 5

More
Less
Retreating

Question 6

Dissymmetry of lift is corrected by blade (Coning, flapping) which (increases,decreases) the ( angle of attack, blade angle) of the advancing blade.

Answer 6

Flapping
Decreases
Angle of attack

Question 7

When flying horizontally to your left, the blade angle of the blade over the nose is at its (greatest, smallest) and the angle of attack is at its (greatest, smallest)

Answer 7

Smallest
Smallest

Question 8

Blowback or flap back is caused by (coning, flapping) of the blades to eliminate ——-

Answer 8

Flapping
Dissymmetry of lift

Question 9

When airspeed increases, a reverse flow area develops on the ——-side of the disc. In this area, blade sections (are, are not) stalled.

Answer 9

Retreating
Are not?

Question 10

As you accelerate through 12-15 kts you do not move the collective up or down. The helicopter will then (climb, remain level, descend) until the influence of ——-.

Answer 10

Climb
Translational lift

Question 11

Transverse flow effect (or inflow roll) is more pronounced at (high, low) airspeed and is caused by (greater, smaller) induced flow being experienced at the rear of the disc than at the front. The helicopter tends to (yawn,roll) to the (advancing, retreating) side.

Answer 11

Low
Greater
Roll
Advancing