Aerodinamics 2 Flashcards

0
Q

Relative Wind

fix wing

A

Direction of the airflow with respect to the wing and is created by the motion of the AC moving through the air

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1
Q

Angle of Incidence

A

formed by the longitudinal axis of the aircraft and the chord of the wing

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2
Q

Angle of Attack

A

Angle between the wing chord line and the direction of the relative wind

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3
Q

Swirling or Burbling

A

when air can no longer flow smoothly over the wings upper surface due to the separation of the boundary layer

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4
Q

Thrust and drag in straight and level flight

A

Drag increases twice as much as increases airspeed

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5
Q

Lift and gravity in straight and level flight

A

if lift becomes less than weight, the AC will descent, and if lift becomes greater than weight, the AC will climb

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6
Q

Wing Area

A

The lift and drag acting on a wing are roughly proportional to the wing area

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7
Q

Airfoil Shape

A

As the upper curvature or camber of an airfoil increased, the lift produced increases.

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8
Q

Basis for all helicopter flight

A

Vertical, forward, backwards, sideward, or hovering

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9
Q

All opposing forces are in balanced

A

At a hover

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10
Q

Relative Wind

Rotary wind

A

moves in a parallel, but opposite, direction to the movement of the airfoil

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11
Q

Rotational Velocity

blade speed

A

near the main rotor shaft is much less, because the distance traveled at the smaller radius is relatively small

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12
Q

Hovering

A

Helicopter maintains a constant position over a selected point

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13
Q

Rotor Tip Vortex

A

The rotor tip vortex reduces the effectiveness of the outer blade portions.

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14
Q

OGE

A

out-of-ground-effect

High-power requirement needed to hover

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15
Q

IGE

A

in-ground-effect

Improved performance encountered when operating near the ground

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16
Q

Induced Flow

A

Produced during OGE, the rotor blades move large volumes of air in a downward direction

17
Q

Induced Flow speed

A

May reach 60 to 100 knots, depending on the size and gross weight

18
Q

Translating Tendency

A

A single rotor helicopter has a tendency to drift laterally to the right

19
Q

Translational Lift

A

Improved rotor efficiency resulting from directional flight

20
Q

Dissymmetry of lift

A

the difference in lift between the advancing half of the rotor disk and the retreating half. Max at 3 o’clock, min at 9 o’clock.

21
Q

Gyroscopic Precession

A

A phenomenon occurring in rotating bodies in which an applied force is manifested 90* ahead of the direction of rotation from where the force was applied

22
Q

Autorotation

A

Some other force must be used to sustain rotor RPM so controlled flight can be continued to the ground

23
Q

Autorotation Phases

A

Entry
Steady-State Descent
Deceleration and Touchdown

24
Entry
Performed following a loss of engine power. Rotor RPM should be stabilized at autorotation RPM (higher than normal RPM)
25
Steady-State Descent
Rate of descent and RPM are stabilized, the helicopter descents at a constant angle. AOA descent normally 17-20 degrees.
26
Deceleration and Touchdown
Must reduce airspeed and rate of descent just before touchdown
27
Torque
the helicopter tends to rotate in the direction opposite the rotor blades
28
Anti-torque rotor
Compensation for torque in the single main rotor helicopter is done by means of a variable pitch, anti torque rotor. 5-15% engine power may be needed to drive the tail rotor.
29
Blade flapping
Up and down movement of the rotor blade which causes elimination of dissymmetry of lift.
30
Retreating Blade Stall
as the speed of the retreating blade decreases with forward speed, the blade AOA must be increased to equalize lift throughout the rotor disk area
31
Produce blade stall at high forward speeds
``` High blade loading Low rotor RPM High density altitude Steep or abrupt turns Turbulent air ```
32
Warnings of approaching retreating blade stall
Abnormal vibration Pitch up of the nose Tendency for the helicopter to roll in the direction of the stalled side
33
Prevent blade stall
``` Fly slower then normal: DA is much higher then standard Carrying Max gross loads Flying high drag configurations The air is turbulent ```
34
Blade stall may be eliminated by..
Decrease collective pitch Decrease the severity of the maneuver Gradually decrease airspeed Increase rotor RPM
35
Blade lead and lag
Fully articulated rotors have hinged blades that are free to move fore and aft in the plane of rotation independent of the other blades in the system.
36
Coriolis Force
Causes blades to lead and lag
37
Conservation of Angular Momentum
A rotating body will continue to rotate with the same rotational velocity until some external force is applied to change the speed of rotation
38
Settling with power
Can occur at any airspeed or altitude whenever power required exceeds power available, preventing level flight.
39
Vortex Ring State
May develop at any ALT or gross weight when the airspeed is bellow translational lift and rate if descent is high (excess of 300ft/min)