Chapter 14 Climb and Descent Aerodynamics Questions and Answers latest updated

Chapter 14 Climb and Descent Aerodynamics Questions and Answers latest updated If the TAS is 100 kt on a glide slope of 3◦, the rate of descent is: (a) 530 fpm In a glide descent at the optimum speed, the effect that increasing the nose-down pitch angle has on the glide distance is that: (b) it decreases The effect that increased mass has on a glide descent is: (b) it increases the vertical and the horizontal speeds Two identical aeroplanes are descending at idle thrust and the optimum angle of attack but at different masses. Which of the following statements is true? (c) The vertical and forward speeds of the heavier aeroplane will be greater. Which of the following combinations of characteristics will affect the glide angle? (a) configuration and angle of attack In a glide descent at the optimum gliding speed, if the pilot increases the pitch attitude the glide distance will: (c) decrease In a glide, at minimum glide angle speed, at a lower mass at the same speed (i) the rate of descent will . . . . . . . . . (ii) the glide angle will . . . . . . . . . (iii) the Cl/Cd ratio will . . . . . . . (a) (i) increase; (ii) increase; (iii) decrease Which of the following will increase the glide distance? (d) a tailwind Which of the following factors will increase the glide time? (d) decreased aeroplane mass In a glide descent, to fly for the maximum endurance the speed should be that for: (d) the minimum angle of descent What effect does increased aeroplane mass have on a glide descent? (d) The speed for the best angle of descent increases. Which of the following statements for a glide descent at the maximum lift to drag ratio speed is correct? (c) A tailwind component increases the ground distance travelled. Which of the following statements for a glide descent at the maximum lift to drag ratio speed is correct? (b) The higher the gross mass the greater is the speed for descent. The lift coefficient decreases during a glide descent at a constant Mach number because the: (c) IAS increases In a steady descent (descent angle GAMMA) the equilibrium of the forces is given by the formula: (b) T + M sin GAMMA = D Two identical aeroplanes at different masses are descending at idle thrust. Which of the following statements correctly describes their descent characteristics? (a) At a given angle of attack, both the vertical and the forward speeds are greater for the heavier aeroplane. An aircraft has a thrust: mass ratio of 1:4 at take-off. If the lift: drag ratio in the climb is 12:1 the climb gradient will be: (d) 16.7% What is the effect of extending flap on the value of Vx and Vy? (d) Vx decreases and Vy decreases What is the effect of an increased flap setting on the gradient and rate of climb? (d) the gradient of climb decreases and the rate of climb decreases At a constant mass, the effect that an increase of altitude has on the value of Vx and Vy is: (b) Vx constant and Vy decreases For a given power setting in the climb, if the speed is increased: (a) the rate of climb will increase if the speed is below Vy The wind effective climb gradient is approximately equal to: (d) ROC in fpm. ÷ Groundspeed in kt The effect an increase of mass has on the values of the ROC and the climb speeds is: (d) ROC decreases and the climb speeds increase The effect an increase of mass has on the value of Vx and Vy is: (a) Vx increases and Vy increases The speed of Vy is flown to obtain: (d) maximum rate of climb The effect a headwind will have on a climb to a specified altitude, compared with still air, is to: (c) decrease the ground distance travelled An aircraft is climbing at a constant power setting and a speed of Vx. If the speed is reduced and the power setting maintained the climb gradient will (i) . . . . . . . . . . . . . In addition, the rate of climb will (ii) . . . . . . . . . . . : (d) (i) decrease; (ii) decrease Given: Still-air climb gradient 4%; TAS 400 kt; Wind Component 50 kt tail; The ground distance travelled in a climb from 8000 ft to 32 000 ft is: (c) 111 nm Given: A four-engined jet aeroplane weighing 37 500 kg has a lift: drag ratio of 14:1 and a total thrust of 75 000 Newtons. g = 10 m/s. The climb gradient is: (d) 12.86% Given: TAS = 194 kt; ROC = 1000fpm. The climb path is: (a) 3◦ Given: Climb Gradient = 2.8%; Climb Mass = 110 000 kg; Required Climb Gradient = 2.6%. The maximum climb mass to achieve the required gradient is: (c) 118 462 kg Given: A three-engined jet aeroplane has 50 000 Newtons of thrust per engine and a total drag of 72 069 Newtons. The gross gradient required with one engine inoperative is 2.75%. The maximum take-off mass is: (a) 101 567 kg Given: TAS = 194 kt; ROC = 1000 fpm. The climb gradient is: (d) 5% The maximum angle of climb speed for a jet-engined aeroplane is approximately: (b) highest Cl/Cd ratio speed How does the value of Vx vary with wind component? (c) It is not affected by the wind component. Increased mass will cause the climb performance to: (d) degrade Given: Climb gradient = 3.3%; TAS 100 kt; Still air. The approximate ROC is: (b) 330 fpm The speed to fly to obtain the maximum obstacle clearance in the climb is: (d) Vx Whilst in a positive climb: (d) Vx is practically always less than Vy The greatest rate of climb at a constant mass: (a) Decreases with increasing altitude because the thrust available decreases due to the decreased air density. At the same altitude a higher gross mass decreases the gradient and rate of climb, whereas: (c) Vy and Vx are increased A higher ambient temperature: (c) decreases the angle of climb and the rate of climb Which of the following speeds will give the maximum obstacle clearance during a climb? (a) The speed at which the ratio of the rate of climb and the forward speed is maximum Apart from lift, the forces that determine the angle of climb are: (d) mass, drag and thrust How do (i) the maximum angle of climb and (ii) the maximum rate of climb vary with increasing altitude? (c) (i) decrease; (ii) decrease On a twin-engined piston aeroplane with variable-pitch propellers, for a given mass and altitude, Vimd is 125 kt and the holding speed (minimum fuel flow) is 95 kt. The maximum rate of climb speed is: (d) at 95 kt