Theory of flight test 2 (#2) (11,12,13,14,16)|2023 LATEST UPDATE|WITH 100% COMPLETE SOLUTIONS|ALREADY GRADED A

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 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