Aero Ii Ch.7

Front 1

State the relationship between fuel flow, thrust available, thrust required, and velocity for a turbojet airplane in straight and level flight.

Back 1

fuel flow is proportional to its Ta. In order to maintain, equilibrium flight, Ta=Tr, so min. fuel flow is found on the Tr curve. Increasing thrust will increase velocity, thus increasing fuel flow.

Front 2

State the relationship between fuel flow, power available, power required, and velocity for a turboprop airplane in straight and level flight.

Back 2

Fuel flow varies directly with Pa. Min. fuel flow is on Pr curve for equilibrium flight.

Front 3

Define maximum endurance and maximum range.

Back 3

Max endurance: Is the maximum amount of time that an airplane can remain airborne on a
given amount of fuel.
Max Range: Is the maximum distance traveled over ground for a given amount of fuel.

Front 4

State the angle of attack and velocity, compared to L/DMAX, at which turbojet and turboprop airplanes achieve maximum endurance.

Back 4

Turbojet
o Max endurance is found at L/DMAX AOA and velocity for a turbojet.
Turboprop
o Max endurance is found at a velocity less than L/DMAX and an AOA
greater than L/DMAX for a turboprop.

Front 5

State the angle of attack and velocity, compared to L/DMAX, at which turbojet and turboprop airplanes achieve maximum range.

Back 5

Turbojet
o Max range is found at a velocity greater than L/Dmax and an AOA less than
L/Dmax AOA.
Turboprop
o Max range is found at L/Dmax AOA and velocity.

Front 6

Describe the effect of changes in weight, altitude, configuration, and wind on
maximum endurance and maximum range performance and airspeed.

Back 6

Max Endurance
o Decrease with an increase in weight and airspeed increases.
o Increases with an increase in altitude and airspeed increases
o Decreases with a configuration change. Airspeed will decrease with
lowering the flaps, but airspeed will remain the same for lowering the
gear.
o Winds have no effect on max endurance.
Max Range
o Decreases with an increase in weight due to higher fuel flow as a result of
a higher velocity required to produce more lift. Airspeed will increase.
o Increases with an increase in altitude and airspeed increases.
o Decreases with a configuration change. Airspeed will decrease with
lowering the flaps, but airspeed will remain the same for lowering the
gear.
o Headwinds will decrease max range while tailwinds increase max range.

Front 7

Define maximum angle of climb and maximum rate of climb.

Back 7

Max Angle of Climb
o Comparison of altitude gained to distance traveled. Objective is to gain
sufficient altitude to clear obstacles with the least horizontal distance
traveled.
Max Rate of Climb
o Comparison of altitude gain relative to time needed to reach an altitude.
Objective is to gain the greatest vertical distance in the shortest time
possible.

Front 8

State the angle of attack and velocity, compared to L/DMAX, at which turbojet and turboprop airplanes achieve maximum angle of climb.

Back 8

Turbojet
o Max angle of climb occurs at L/Dmax AOA and velocity.
Turboprop
o Max angle of climb occurs at a velocity less than L/Dmax and an AOA
greater than L/Dmax AOA.

Front 9

State the angle of attack and velocity, compared to L/DMAX, at which turbojet and turboprop airplanes achieve maximum rate of climb.

Back 9

Turbojet
o Max rate of climb occurs at velocity greater than L/Dmax and an AOA less
than L/Dmax AOA.
Turboprop
o Max rate of climb occurs at L/Dmax AOA and velocity.

Front 10

Describe the effect of changes in weight, altitude, configuration, and wind on
maximum angle of climb and maximum rate of climb performance and airspeed.

Back 10

An increase in weight, an increase in altitude, a change in configuration will all
decrease both maximum thrust excess and maximum power excess for all aircraft.
Max angle and max rate of climb performance will decrease.
• A headwind will increase Max Angle of Climb because it reaches the same
altitude as before with a smaller distance covered over the ground. Tailwind has
opposite effect.
• Wind does not effect rate of climb performance.

Front 11

Define absolute ceiling, service ceiling, cruise ceiling, combat ceiling, and
maximum operating ceiling.

Back 11

Absolute Ceiling
o Max rate of climb is zero fpm.
• Service Ceiling
o Max rate of climb is 100 fpm.
• Cruise Ceiling
o Max rate of climb of 300 fpm.
• Combat Ceiling
Max rate of climb of 500 fpm.

Front 12

State the maximum operating ceiling of the T-34C.

Back 12

25,000 ft

Front 13

Define maximum glide range and maximum glide endurance.

Back 13

Max Glide range: Gliding as far as possible when an engine fails.
Max Glide Endurance
o Maximize time aloft. Used if you lose an engine within easy reach of a
safe runway, while the runway is being cleared.

Front 14

State the angle of attack and velocity, compared to L/DMAX, at which an airplane achieves maximum glide range.

Back 14

Max glide range and velocity (Vbest) occurs at L/Dmax.
• Vbest is 100 KIAS for the T-34

Front 15

State the angle of attack and velocity, compared to L/DMAX, at which an airplane achieves maximum glide endurance.

Back 15

Max glide endurance velocity is less than L/Dmax velocity and the AOA for max
glide endurance is greater than L/Dmax AOA.

Front 16

Describe the effects of changes in weight, altitude, configuration, wind, and
propeller feathering on maximum glide range and maximum glide endurance
performance and airspeed.

Back 16

Increasing the weight will cause the airplane to fly faster and descend
faster, but still glide the same distance.
o Increase in altitude will increase Max Glide Range.
o Headwind decreases groundspeed and thus decreases Maximum Glide
Range. Tailwind increases Max Glide Range.
o Glide Range will decrease with a configuration change
o Feathering the propeller increases glide range.
Max Glide Endurance
o Decreases with an increase in weight.
o Increases with an increase in altitude.
o Wind has not effect on glide endurance.
o Decreases with a configuration change.
o Feathering the propeller increases glide endurance.

Front 17

Define the regions of normal and reverse command as they relate to maximum
endurance angle of attack and velocity.

Back 17

Normal Command
o Velocities above maximum endurance AOA are referred to as the region
of normal command.
o Characterized by airspeed stability.
• Reverse Command
o Velocities below maximum endurance AOA are referred to as the region
of Reverse Command.
o Characterized by airspeed instability.

Front 18

Describe the relationship between velocity and throttle setting required to
maintain level flight within the region of normal and reverse command.

Back 18

Normal Command
o Velocities and throttle settings are directly related.
• Reverse Command
o Velocities and throttle settings are inversely related.
o The slower you fly, the more thrust/power you need.