In what way is the longitudinal stability affected by the degree of positive camber of an aerofoil?
No effect
one of the factors that limits the
... [Show More] maximum aft position of the CG is
minimum value of the sick force per g
the aft movement of the CP during acceleration through the transonic flight regime will
increase the static longitudinal stability
how does the exterior appearance of an aeroplane change when it is trimmed for a speed increase?
elavator deflection is increased further downward by the upward deflection of the trim tab
aft movement of the CG will
increase the elevator-up effectiveness
sensitivity for a spiral dive will occur when
the static directional stability is positive and the static lateral stability is relatively weak
in straight and level flight the value of manoeuvre stability is 150 N/g. to achieve load factor of 2.5 the increase of stick force necessary is
225
the effect that the use of trim to accommodate a speed decrease has on the appearance of the plane is
the elevator is deflected further upward by a downward deflected trim tab
the CG of a stavle plane is located
ahead of the neutral point by a sufficient margin
in a sideslip to the right, a plane that has static directional stability, initially the:
nose tends to move to the right
static longitudinal stability is created by
the CG being located ahead of the neutral point
the lateral static stability is decreased by
anhedral
a statically unstable plane is
never dynamically stable
a plane that has positive static stability
may be dynamically stable, neutral or unstable
the effect that a positive wing sweep has on directional static stability is that it has
a stabilising effect
the greatest positive contribuion to the longitudinal static stability is provided by
the horizontal tailplane
a CG located beyond the aft limit leads to
an unacceptably low value of the maneuver stability
if CG is located in a forward position then the elevator deflection for a maneuver with a load factor greater than 1 will be
larger
the lateral static stability of a plane is increased by
high wing, sweep back, large and high vertical tail
the CG is aft of the CP straight and level flight can only be maintained when the horizontal tail loading is
upward
the maneuverability of a plane is best when the
CG is on the aft limit of the CG envelope
rearward movement of the CG
creates a tendency to dutch roll
a plane that is statically unstable
can never by dynamically stable
longitudinal static stability is provided by the
horizontal stabiliser
if the total moment of a plane is not zero it will rotate about the
CG
the position of the CG that produces the greatest stability is
on the forward limit of the envelope
a swept wing causes
positive dihedral effect
when landing a plane with excessive lateral stability in a crosswind it will require
more aileron into wind
the aerodynamic center is the point at which
the pitching moment is constant for all normal angles of attack
a plane with positive static stability is
dynamically neutral, stable or unstable
the elevator deflection required to counter a forward CG movement for a maneuver having a load factor greater than one is
increased
the position that the CG should be located is
a sufficient margin ahead of the neutral point
wing dihedral
increases the lateral static stability
the effect of having the CG on the forward limit and full nose down trim on rotation at takeoff is that the
stick forces will increase
which of the following produces the greatest maneuverability
an aft CG position
the wing shape least sensitive to turbulance is
swept wings
the yaw damper corrects which plane behavior
dutch roll
which motions interact in a dutch roll
roll and yaw
which of the following statements is correct
dynamic stability is only possible when the plane is statically stable about the relevant axis
the essential requirement for dynamic stability is
positive static stability
the "short period mode" is an
oscillation about the lateral axis
a plane that is longitudinally statically unstable is simultaneously dynamically
unstable
dynamic longitudinal stability requires
positive static longitudinal stability
in a phugoid
dampig is weak
a plane that has positive static stability is dynamically...........
either neutral, stable or unstable
a plane is prone to spiral divergence if it has the following conditions
positive directional stability and weak lateral stability
which of the following conditions make an aircraft prone to spiral divergence
positive directional stability, weak lateral stability
short period oscillation is
oscillation in pitch
the tendency to dutch roll increases with
increased static lateral stability
sensitivity to the dutch roll is increased by
increased static lateral stability
the load factor that determines Va is the
maneuvering limit load factor
the data that may be obtained from a beffet onset boundary chart is
the low speed and the high speed buffet mach numbers for various masses and altitudes
the maneuvering load factor positive limit for a utility category light plane in the clean configuration is
4.4
two planes a different masses execute a 20 degree banked turn at 150 kt IAS. the heavier plane will
turn at the same radius as the lighter plane
the limiting load factor for a large transport plane i the maneuvering diagram is
2.5
the buffet margin
increases during a constant IAS descent
Va is
the maximum speed at which maximum up-elevators deflection is permitted
Vmo
should not be greater than Vc
the turn indicator shows a right turn and the slip indicator is left of the neutral position. the action required to coordinate the turn is
increase the right bank
exceeding va by a small amount may result in
permanent structural damage if the elevator is deflected fully up
if there is only one fixed value of Va it is
the speed at which the plane will stall at the maneuvering load factor at the MTOM
the bank angle to be used in a rate one turn depends on the
TAS
if all other factors remain constant, which of the following has the effect of increasing the load factor
vertical gust
is it permissible for a transport plane to exceed the "buffet-onset mach number"
no
the speed limiting the right side of the gust maneuver envelope is
Vd
the formula to determine wing loading is
mass/wing area
to maintain altitude and airspeed during a turn the pilot must
increase the angle of attack and increase the thrust
a heavy plane and a light plane enter a turn at the same TAS and with the same bank angle. the radius of turn of the heavy plane is ...... that of the light plane
the same as [Show Less]