8. Basic aerodynamics - Q&A
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The vertical fin of a single engined aircraft is
- parallel with both the longitudinal axis and vertical axis.
- parallel with the longitudinal axis but not the vertical axis.
- parallel with the vertical axis but not the longitudinal axis.
isn't the fin for single engine aircraft is parallel to virtical axis and offset to the left of the longitudinal axia,
What is the main purpose of a frise aileron?
- Increase drag on the up going aileron.
- Decrease drag on the up going wing surface.
- Help the pilot overcome aerodynamic hinge loads.
frise aileron produces more drag on up going wing or is it to the up going aileron.little confused..
During a climb from a dive
- the thrust required is greater than required for level flight.
- the thrust required is lower than for level flight.
- the thrust required is the same as for level flight.
plz explain
During a turn, the stalling angle
- increases with bank angle.
- decreases noticeably.
- remains the same.
plz explan
Which wing increases drag when the ailerons are moved?
- Both wings increase drag but the wing with the up-going aileron has more.
- Both wings experience an equal increase in drag.
- Both wings increase drag but the wing with the down-going aileron increases more.
plz explan
A balance tab
- effectively increases the total area of the control surface.
- assists the pilot to move the controls.
- is used to trim the aircraft about the appropriate axis.
but some aircrafts have the balance tab adjusted manualy to help keeping the aircraft to the appropriate axis, doesn't it?
An aircraft flying in "ground effect" will produce
- more lift than a similar aircraft outside of ground effect.
- less lift than a similar aircraft outside of ground effect.
- the same lift as a similar aircraft outside of ground effect.
What is ''ground effect''?
With a trailing edge flap being lowered, due to rising gusts, what will happen to the angle of attack?
- Tend to decrease.
- Stay the same.
- Tend to increase.
Someone can show me why the angle of attack tend to increase?
An aircraft flying below the tropopause descends at a constant True Airspeed, its Mach. No. will
- stays constant.
- rise.
- decrease.
why? If TAS is costant the Mach No. will be constant for me. Help?
The ISA
- defines a standard atmosphere model.
- is referenced from the equator.
- is taken from 45 degrees latitude.
I think The ISA assume a standard day is the right answer
Induced drag
- is equal to the profile drag at Vmd.
- is equal to the profile drag at the stalling speed.
- is never equal to the profile drag.
Vmd ?
With the flaps lowered, the stalling speed will
- increase.
- decrease.
- not change.
help!!
For an aircraft climbing at a constant IAS the Mach number will
- increase.
- decrease.
- remain constant.
help!!
When the trailing edge flaps are lowered, the aircraft will
- pitch nose up.
- pitch nose down.
- yaw to one side.
how come?
An aircraft flying above the tropopause descends at a constant True Airspeed, its Mach No. will
- remain the same.
- decrease steadily.
- increase at a constant rate.
please explain.
Aspect ratio is given by the formula:
- Mean Chord / Span.
- Span^2 / Area.
- Span^2 / Mean Chord.
How come?
Vortex generators are fitted to
- move transition point rearwards.
- move the transition point forwards.
- delay the onset of boundary layer separation.
As i understand , a transition point is a point where air flow changes from laminar to turbulent, so what's the benefit of moving the transition point forward? i think the answer must be reviewed and i think it should be " rearwards"..
An aircraft will have
- less gliding distance with a higher payload.
- more gliding distance with a higher payload.
- the same gliding distance if it has more payload.
please explain .
Other than spoilers, where are speed brakes located?
- Underneath the fuselage belly near the main landing gear doors.
- Either side of the fuselage or on the wing.
- Mounted on the wing trailing edge inboard section.
need F1.
For a given IAS an increase in altitude will result in
- an increase in induced drag.
- no change in the induced drag value.
- an increase in profile drag.
i thought induced drag is inversely proportional to altitude?
On a very hot day with ambient temperature higher than ISA, the pressure altitude is 20,000 ft. How much will the density altitude be?
- exactly 20,000ft.
- greater than 20,000ft.
- less than 20,000ft.
Why is this?
Weight is equal to
- mass * acceleration.
- mass * gravity.
- volume * gravity.
gravity=mass×acceleration which is 9.8m/s＊s,the correct should be A
When the weight of an aircraft increases, the minimum drag speed
- decreases.
- increases.
- is unaffected.
can anyone clarify this? thanks :)
The power required at low altitude for a given IAS is
- unchanged with altitude.
- higher.
- lower.
Power is dependant on TAS and not IAS
Power =velocity *drag
Low wing loading
- increases stalling speed, landing speed and the landing run.
- increases lift, stalling speed and overall maneuverability.
- decreases stalling speed, landing speed and landing run.
what is low wing loading