JNTU B.Tech II FLIGHT MECHANICS-I Previous Question Paper (December - 2018 - R15)

Mention types of thrust producing engines.

Discuss the thrust variation with speed of aircraft fitted with propeller engine.

What do you understand by word performance of aircraft?

How optimum cruise speed for an aircraft is decided?

Explain the following: i) Specific thrust ii) Thrust specific fuel consumption.

Discuss different types of aircraft ceilings.

What is baulked landing?

How ground influences Takeoff and Landing?

What corrections are adopted for collected date of weight and temperature?

How route analysis is carried out? Explain.

Enumerate the effects of altitude on the following: i) Thrust produced ii) propulsive power iii) Specific fuel consumption.

The thrust of a jet engine decreases as flight velocity increases. Maximum thrust at zero velocity at sea level is 250 kN. Calculate the thrust at an altitude of 3km at Mach 0.7.

What is drag polar? From first principles, show that velocity for level flight is function of thrust loading, wing loading and drag polar.

An airfoil with chord of 1.5m length is inclined an angle of 4 degree with free stream. If flow velocity is 38 m/s at standard sea level, calculate the total drag per unit span. Take viscosity coefficient at sea level, 1.7894 × 10^-5 kg/m.s.

Describe the following for Jet and Propeller engines: i) Thrust required and thrust available ii) Power required and power available

A twin turbo fan aircraft weighing 380kN is moving at a speed of 150m/s at an altitude of 12 km above sea level. Calculate the thrust required. Take plan form area 90m², aspect ratio 5.92, zero lift drag coeff. 0.014, K=0.09.

An airplane propelled by propeller engine in on cruise phase of flight. Explain on how to optimum cruising performance.

Calculate lift to drag ratio for an airplane of 420kN weight, cruising at a speed of 200m/s, and has S = 4.5, C_D,0 = 0.013, K = 0.075.

Bring out any five differences between glide and powered decent.

Calculate the max range an aircraft can cruise at an altitude of 15km, if its usable fuel weight is 130kN. The thrust specific fuel consumed is 0.65 N per hour per Newton thrust.

An aircraft propelled by jet engine is set to climb to desired altitude. Discuss how to optimize the climb with regard to climb angle and rate of climb.

Calculate minimum velocity an airplane can cruise at desired altitude with the following date. Wing loading 4000 N/m², thrust to weight 0.4, C_D,0 = 0.012, K = 0.08, density 0.98 kg/m³.

Briefly, discuss on how landing phase is critical.

Calculate approach and flare distances of an airplane weighing 400kN landing at standard sea level. Take friction coefficient 0.38 and a approach angle 3.5 degrees.