Aero 1-6
Aerodynamic 081
Aerodynamic 081
Set of flashcards Details
| Flashcards | 34 |
|---|---|
| Language | English |
| Category | Physics |
| Level | Other |
| Created / Updated | 07.12.2016 / 08.12.2016 |
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When flaps are deployed at constant AoA, lift coefficientw will...
increase!
Flap selcetion at constant IAS in S&L flight will increase the...
max. lift coefficient (CLmax) and the drag.
Difference between the effects of flap and slat asymettry is that...
flaps asymmetry causes a large rolling moment at any speed,
whereas slat asymmetry causes a large difference in CLmax.
The use of slat in leading edge of the wing enables the aeroplane to fly at a slower speed because...
it delays the stall to a higher angle of attack.
When spoliers are extended the part of the wing which they are mounted...
experiences a reduction in lift, which generates the desired rolling moment, additionally
there is a local increase in drag, which suppresses adverse yaw.
What happens with drag and lift -> wing spoiler extension in S&L flight, the speed and load factor are constant...
drag increases,
lift remains unaffected
The rotation about the NORMAL axis is...
yawing!
The elevtaor deflection required for a given manoeuvre will be:
smaller at high IAS when compared to low IAS.
An aircraft is approaching to land with CG at the forward limit. It will be:
difficult to flare and VREF will be higher than normal.
I. The effects of stabiliser trim runaway are more serious.
II. A jammed trim tab causes less control difficultly.
I. correct and II. correct
Left rudder input will cause...
left yaw about the vertical axis and left roll about the longitudinal axis.
The primary roll controls on a conventional airplane are...
the ailerons.
An airplan is provided with Spoilers and both inboard and outboard ailerons.
Roll control during cruise is provided by...
inboard ailerons and roll spoilers.
Which phenomenon is counteracted with differential aileron deflection?
Adverse yaw.
A spring tab (character)...
at high IAS it behaves like a servo tab
The reason for having a trim system on powered assisted flying control is...
enables the stick force to reduce to zero.
Some airplanes have spring tabs mounted into the control system:
This is provide:
a reduction in the pilots effort to move the controls against high airloads!
What should be usually done to perform a landing with stabilizer jammed in the cruise flight position?
choose a higher landing speed than normal and/ or
use a lower flapsetting for landing.
The most important factor for (THS) Trimmable Horizontal Stabilizer is the...
position of aeroplanes C.G
(Centre of Gravity)
The effect on landing speed when THS jams at high IAS is:
in most cases a higher than normal landing speed!
* I. A stabilizer trim is more suitable to cope with the large trim changes generated by the high lift devices on most jet transport airplanes
thats correct
An aft CG shift ..... static longitudinal stability.
An aft CG shift DECREASES static longitudinal stability.
Longitudinal stability is directly influenced by ......
Longitudinal stability is directly influenced by "C.G. position"
A C.G. location beyond the aft limit leads to ......
an unacceptable low value of the manoeuvre stability (stick force per g, Fe / g)
A forward CG shift ..... static londitudinal stability.
A forward CG shift increases static londitudinal stability.
Static directional stability is ....
Static directional stability is the tendency of an aeroplane to recover from a skid with the rudder free.
normal stable aeroplane:
the CG is with a sufficient minimum margin ahead of the neutral point of the aeroplane.
The best manoeuvrebality is when:
The best manoeuvrebality is when CG is on the aft C.G. limit.
The effect of positive wing sweep on static directional stabilty :
The effect of positive wing sweep on static directional stabilty:
----> Stabilizing effect.
A dorsal fin... (large text)
increases the contribution of the vertical tail plane to the static dircetional stability, in particular at large angles of sideslip...
A positive static lateral stability in the tendency of an airplane:
roll to the left in case of a sideslip.
(with the airplane nose pointing to the left of incoming flow)
The effect of ventral fin on static stability of airplane:
1. longitudinal
2. lateral
3. directional
1. longitudinal = no effect
2. lateral = negative
3. directional = positive
The effect of high wing with zero dihedral is:
positive dihedral effect.
I. A requirement for positive static longitudinal stability of an aeroplane is, that the neutral point is behind the CG.
II. A wing with the positive camber provides a positive contribution to static longitudinal stability , when the CG is in front of the
a.c. of the wing.
I. static longitudinal stability = neutral point is behind CG.
II. When CG is in front of a.c. of the wing, it provides a positive contribution to static longitudinal stability)
