8. Basic aerodynamics - Q&A
131 questions found
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Vortex generators are fitted to
- move transition point rearwards.
- move the transition point forwards.
- delay the onset of boundary layer separation.
transition point forward with the help of vortex gen. how it helps.......... confuses me??????
Supersonic air going through an incipient shock wave will decrease its speed and
- decrease temperature and increase density.
- increase temperature and decrease density.
- increase temperature and increase density.
explan
What effect would a forward CG have on an aircraft on landing?
- Increase stalling speed.
- Reduce the stalling speed.
- No effect on the landing.
Can anyone explain?
In straight and level flight, the angle of attack of a swept wing is
- less than the aircraft angle to the horizontal.
- more than the aircraft angle to the horizontal.
- the same as the aircraft angle to the horizontal.
can someone explain ?
An undercarriage leg in flight produces 3 lbs of drag at 100kts. If speed is increased to 200kts the drag would be
- 12 lbs.
- 9 lbs.
- 6 lbs.
how to calculate...
The speed of air over a swept wing which contributes to the lift is
- less than the aircraft speed.
- the same as the aircraft speed.
- more than the aircraft speed.
isnt upper surface has more velocity than the relative wind?
With respect to differential aileron control, which of the following is true?
- The up going and down going ailerons both deflect to the same angle.
- The up going Aileron moves through a smaller angle than the down going aileron.
- The down going aileron moves through a smaller angle than the up going aileron.
isnt it vice versa?
If an aircraft in level flight loses engine power it will
- pitch nose up.
- pitch nose down.
- maintain pitch until drag builds up.
Isn't it should temporarily nose up before eventually going nose down since CoP is behind CoG, and with no thrust CoP decreases the lift(behind CoG) causing nose up?
An aircraft left wing is flying low. The aileron trimmer control to the left aileron trim tab in the cockpit would be
- moved up causing the left aileron to move up.
- moved up causing the left aileron to move down.
- moved down causing the left aileron to move down.
Is this question is about STABILITY or the position of trim tab/aileron ?
A wing develops 10,000N of lift at 100knots. Assuming the wing remains at the same angle of attack and remains at the same altitude, how much lift will it develop at 300knots?
- 900,000N.
- 90,000N.
- 30,000N.
how to calculate??
In a steady climb at a steady IAS, the TAS is
- more than IAS.
- the same as IAS.
- less than IAS.
please explain...
Supersonic air passing through a divergent duct causes the
- pressure to increase, velocity to increase.
- pressure to increase, velocity to decrease.
- pressure to decrease, velocity to increase.
Isn't in supersonic air flow, everything is vice versa?
Downward displacement of an aileron
- increases the stalling angle of attack for that wing.
- decreases the angle at which its wing will stall.
- has no effect on its wing stalling angle, only on stalling speed.
how come aileron effect the stall?
In a turn the up-going wing causes a
- de-stabilizing effect due to increased AoA.
- de-stabilizing effect due to decreased AoA.
- stabilizing effect due to decreased AoA.
Up going wing means down going aileron for that wing, down going aileron means more lift i.e more AoA and more drag?
help please!
On a very humid day, an aircraft taking off would require
- a shorter take off distance.
- a longer take off run.
- humidity has no measurable effect on take off run length.
high humidity = high density
so the lift will high..
short runway are used..
correted me if i mistaken
Which of the following types of drag increases as the aircraft gains altitude?
- Interference drag.
- Parasite drag.
- Induced drag.
please explain...
Lateral stability is about the
- longitudinal axis.
- normal axis.
- vertical axis.
Help...
An elevator provides control about the
- longitudinal axis.
- lateral axis.
- horizontal stabilizer.
function of elavator is to pitch up or pitch down....
so its at horizontal stabilizer.... and the answer is wrong
The temperature to which humid air must be cooled at constant pressure to become saturated is called
- relative humidity.
- dew point.
- absolute humidity.
i think the answer is about humidity..
so its between absolute humidity and ralative humudity
A delta wing has
- a lower stall angle than a straight wing.
- a higher stall angle than a straight wing.
- the same stall angle than a straight wing.
help....
i want to know about delta wing lift,drag and stall
Mach number is
- the ratio of the aircrafts TAS to the speed of sound at the same atmospheric conditions.
- the ratio of the aircrafts IAS to the speed of sound at the same atmospheric conditions.
- the ratio of the aircrafts TAS to the speed of sound at sea level.
what TAS mean???
A stall warning device must be set to operate
- at a speed just above stalling speed.
- at a speed just below stalling speed.
- at precisely the stalling speed.
bollocks
Aspect ratio is given by the formula:
- Mean Chord / Span.
- Span^2 / Area.
- Span^2 / Mean Chord.
not too clear about the answer
On a swept wing aircraft if both wing tip sections lose lift simultaneously the aircraft will
- yaw uncontrollably.
- pitch nose up.
- pitch nose down.
loss of lift = nose drop, how come in this case it's not so?
thx
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.
i think the down going wing(i.e.up going aileron) instead of down going aileron (i.e.up going wing) increases more drag