Atmospheric Flight Mechanics

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aircraft starts gliding in power-off condition at an altitude of 4 km. Given that the maximum lift to drag ratio of the aircraft is 15, the maximum glide range that the aircraft can cover, measured along the ground, is ________ km (rounded off to the nearest integer).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

A gas mixture at a pressure of 800 kPa and a density of 5 kg/m3 enters a turbine stage. The temperature of the gas at the nozzle exit and the stage exit are 790 K and 750 K, respectively. Assume the specific heats are constant for the gas mixture in the range of temperatures considered. The specific heat at constant pressure is 0.72 kJ/kg-K and the ratio of specific heats is 1.33. The value of the degree of reaction of the turbine stage is ________ (rounded off to 2 decimal places).

Subtopic: Climb, Glide, Ceiling & Turn Performance

For a general aviation airplane, which one of the following has a destabilizing effect on its static roll stability?

Subtopic: Climb, Glide, Ceiling & Turn Performance

A general aviation airplane is flying at an altitude of 5000 m. The indicated airspeed is 250 km/h. Assume that there are no instrument errors and position errors. Neglecting compressibility effects, which one of the following options is FALSE?

Subtopic: Climb, Glide, Ceiling & Turn Performance

A general aviation airplane is initially in steady and level flight. The stability coefficient $\partial$Cm $\partial$q (Cm is the airplane pitching moment coefficient and q is the pitch rate) is negative. The airplane is perturbed with a small nose-up constant pitch rate. Assume that the horizontal tail does not stall during the perturbation, and unsteady effects are neglected. When compared to steady and level flight condition, which of the following statements is/are true during the perturbed motion?

Subtopic: Climb, Glide, Ceiling & Turn Performance

A general aviation airplane is gliding with a speed Vg at minimum glide angle. Which of the following statements is/are true?

Subtopic: Climb, Glide, Ceiling & Turn Performance

In a low-speed airplane, a venturimeter with 1.3:1 area ratio is used for airspeed measurement. The airplane's maximum speed at sea level is 90 m/s. If the density of air at sea level is 1.225 kg/m^3, the maximum pressure difference between the inlet and the throat of the venturimeter is ________ kPa (rounded off to two decimal places).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

While taking off, the net external force acting on an airplane during the ground roll segment can be assumed to be constant. The airplane starts from rest. SLO and VLO are the ground roll distance and the lift-off speed, respectively. $\alpha$VLO ($\alpha$ > 0) denotes the airplane speed at 0.5 SLO. Neglecting changes in the airplane mass during the ground roll segment, the value of $\alpha$ is _____ (rounded off to two decimal places).

Subtopic: Drag Polar & Aircraft Performance Equations

Which one of the following figures represents the drag polar of a general aviation aircraft?

Subtopic: Climb, Glide, Ceiling & Turn Performance

Which of the following statements about a general aviation aircraft, while operating at point Q in the V-n diagram, is/are true?

Subtopic: Climb, Glide, Ceiling & Turn Performance

An airplane experiences a net vertical ground reaction of 15000 N during landing. The weight of the airplane is 10000 N. The landing vertical load factor, defined as the ratio of inertial load to the weight of the aircraft, is __________ (rounded off to 1 decimal place).

Subtopic: Standard Atmosphere Properties

As per the International Standard Atmosphere model, which one of the following options about density variation with increase in altitude in the isothermal layer is correct?

Subtopic: Drag Polar & Aircraft Performance Equations

Which of the following statements about absolute ceiling and service ceiling for a piston-propeller aircraft is/are correct?

Subtopic: Climb, Glide, Ceiling & Turn Performance

An airplane weighing 40 kN is landing on a horizontal runway during which it is retarded by an arresting cable mechanism. The tension in the arresting cable at a given instant, as shown in the figure, is 100 kN. Assuming that the thrust from the engine continues to balance airplane drag, the magnitude of horizontal load factor is ________. (round off to one decimal place)

Subtopic: Drag Polar & Aircraft Performance Equations

An airplane with wing planform area of 20 m2 and weight 8 kN is flying straight and level with a speed of 100 m/s. The total drag coefficient is 0.026 and the air density is 0.7 kg/m^3. The total thrust required to introduce a steady climb angle of 0.1 radians is ____ N. (round off to the nearest integer)

Subtopic: Climb, Glide, Ceiling & Turn Performance

The maximum permissible load factor and the maximum lift force coefficient for an airplane is 7 and 2, respectively. For a wing loading of 6500 N/m2 and air density 1.23 kg/m^3, the speed yielding the highest possible turn rate in the vertical plane is ___________ m/s. (round off to the nearest integer)

Subtopic: Climb, Glide, Ceiling & Turn Performance

The service ceiling of an airplane is the altitude

Subtopic: Standard Atmosphere Properties

For International Standard Atmosphere (ISA) up to $11\text{ km}$, which of the following statement(s) is/are true?

Subtopic: Climb, Glide, Ceiling & Turn Performance

An unpowered glider is flying at a glide angle of 10 degrees. Its lift-to-drag ratio is (round off to two decimal places).

Subtopic: Climb, Glide, Ceiling & Turn Performance

A uniform rigid prismatic bar of total mass $m$ is suspended from a ceiling by two identical springs as shown in the figure. Let $\omega_1$ and $\omega_2$ be the natural frequencies of mode I and mode II respectively ($\omega_1 < \omega_2$). The value of $\omega_2 / \omega_1$ is ______ (rounded off to one decimal place).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Rocket Propulsion (Tsiolkovsky Rocket Equation & Specific Impulse). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Strength of Materials & Elasticity (Airframe Structural Analysis & Trusses). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Structural Dynamics & Aeroelasticity (Flutter Phenomenon & Divergence Speed). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

Which of the following statement(s) is/are true? (A) Service ceiling is higher than absolute ceiling for a piston-propeller aircraft. (B) For a given aircraft, the stall speed increases with increase in altitude. (C) Everything else remaining the same, a tailwind increases the range of an aircraft. (D) For a jet aircraft constrained to fly at constant altitude, there exists an altitude where its range is maximum.

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Atmospheric Flight Mechanics (Range and Endurance of Jet & Propeller Aircraft). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Thermodynamic Cycles of Gas Turbines (Brayton Cycle with Real Component Efficiencies). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Inlets, Combustors & Nozzles (Convergent & Convergent-Divergent (C-D) Nozzles). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Compressors and Turbines (Centrifugal Compressors). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Inlets, Combustors & Nozzles (Combustor Design & Flame Stabilization). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Rocket Propulsion (Solid, Liquid & Hybrid Rocket Engines). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Compressors and Turbines (Axial Flow Gas Turbines & Blade Cooling). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Strength of Materials & Elasticity (Euler Buckling of Columns & Energy Methods). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Thin-Walled Structures (Torsion of Multi-Cell Thin-Walled Tubes). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Thin-Walled Structures (Tension Field Beams & Wagner Beams). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Structural Dynamics & Aeroelasticity (Free & Forced Vibrations of Continuous Beams). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Aerospace Materials & Fatigue (Aluminum, Titanium & Aerospace Alloys). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Aerospace Materials & Fatigue (Damage Tolerance & Non-Destructive Testing). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Rocket Propulsion (Tsiolkovsky Rocket Equation & Specific Impulse). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Strength of Materials & Elasticity (Airframe Structural Analysis & Trusses). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Thin-Walled Structures (Shear Flow in Open and Closed Thin-Walled Beams). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

A single engine, propeller driven, general aviation airplane is flying in cruise at sea- level condition (density of air at sea-level is 1.225 kg/m') with speed to cover maximum range. For drag coefficient Cp = 0.025 + 0.049 Ci? and wing loading W/S = 9844 N/m?, the speed of the airplane is _ m/s (round off to one decimal place).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Inlets, Combustors & Nozzles (Convergent & Convergent-Divergent (C-D) Nozzles). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Compressors and Turbines (Centrifugal Compressors). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Inlets, Combustors & Nozzles (Combustor Design & Flame Stabilization). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Rocket Propulsion (Solid, Liquid & Hybrid Rocket Engines). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Compressors and Turbines (Axial Flow Gas Turbines & Blade Cooling). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Strength of Materials & Elasticity (Euler Buckling of Columns & Energy Methods). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Thin-Walled Structures (Torsion of Multi-Cell Thin-Walled Tubes). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Thin-Walled Structures (Tension Field Beams & Wagner Beams). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Structural Dynamics & Aeroelasticity (Free & Forced Vibrations of Continuous Beams). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Aerospace Materials & Fatigue (Aluminum, Titanium & Aerospace Alloys). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Aerospace Materials & Fatigue (Damage Tolerance & Non-Destructive Testing). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Climb, Glide, Ceiling & Turn Performance

Which of the following graphs represents the response of a dynamically unstable airplane? response

Subtopic: Range and Endurance of Jet & Propeller Aircraft

The power-off glide range for an airplane with a maximum Lift to Drag ratio of 18, when the glide starts from an altitude of 4 km above ground level, is _________ km (round off to the nearest integer).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

For an airplane flying in a vertical plane, the angle of attack is $3^\circ$, the horizontal and vertical components of velocity in wind axes are 300 km/h and 0 km/h, respectively. If the pitch angle is $9^\circ$, the climb angle of the airplane is _________ degrees (round off to the nearest integer).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An airplane is in steady level flight with a true air speed of 50 m/s. The ambient air density and ambient static pressure are 1.2 kg/m$^3$ and $1.0 \times 10^5$ N/m$^2$, respectively. If the flow is incompressible, the equivalent air speed (in m/s) of the airplane is _________ (round off to 2 decimal places). (Take sea level standard air density $\rho_0 = 1.225$ kg/m$^3$)

Subtopic: Climb, Glide, Ceiling & Turn Performance

The airplane shown in the figure starts executing a symmetric pull-up maneuver from steady level flight at $V = 100$ m/s. If the pull-up radius of curvature is $R = 500$ m and $g = 9.81$ m/s$^2$, the load factor $n$ experienced by the airplane is _________ (round off to 2 decimal places).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

A propeller driven airplane has a gross take-off weight of 4905 N with a wing area of 6.84 m$^2$. Assume that the lift coefficient at take-off is 1.2 and air density is 1.225 kg/m$^3$. The lift-off speed (in m/s) of the airplane multiplied by 100 is approximately _________ (round off to the nearest integer).

Subtopic: Climb, Glide, Ceiling & Turn Performance

As shown in the figure, a rigid slab CD of weight $W$ (distributed uniformly along its length) is hung from a ceiling using three vertical cables of identical length and cross-sectional area. The central cable is made of steel (Young's modulus = $3E$) and the other two outer cables are made of aluminium (Young's modulus = $E$). The percentage of the total weight taken by the central cable is _________ % (round off to the nearest integer).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

The highest limit load factor experienced by a civil transport aircraft is in the range

Subtopic: Standard Atmosphere Properties

An aircraft with a gross weight of 2000 kg , has a speed of 130 m/s at sea level, where the conditions are: 1 atmosphere (pressure), 288 K (temperature), and 1.23 kg/m^3 (density). The speed (in m/s) required by the aircraft at an altitude of 9000 m, where the conditions are: 0.31 atmosphere, 230 K, and 0. 47 kg/m^3, to maintain a steady, level flight is ________ (accurate to two decimal places).

Subtopic: Climb, Glide, Ceiling & Turn Performance

Gross weight of an airplane is 7000 N, wing area is 16 m^2, and the maximum lift coefficient is 2.0. Assuming density at the altitude as 1.23 kg/m^3, the stall speed (in m/s) of the aircraft is _________ (accurate to two decimal places).

Subtopic: Climb, Glide, Ceiling & Turn Performance

Gross weight of an airplane is 7000 N, wing area is 16 m$^2$, and the maximum lift coefficient is 2.0. Assuming air density at the altitude as 1.23 kg/m$^3$, the stall speed (in m/s) of the aircraft is _________ (accurate to two decimal places).

Subtopic: Climb, Glide, Ceiling & Turn Performance

An aircraft landing gear can be idealized as a single degree of freedom spring-mass-damper system. The desirable damping characteristics of such a system is:

Subtopic: Range and Endurance of Jet & Propeller Aircraft

The equation x^2 + 5x + 4y = 0 has a solution y (x) that is:

Subtopic: Drag Polar & Aircraft Performance Equations

A conventional low speed aircraft had the following aerodynamic characteristics: wing area $S = 20$ m$^2$, weight $W = 30000$ N, and zero-lift drag coefficient $C_{D0} = 0.02$. At sea level with $\rho = 1.225$ kg/m$^3$, if the thrust required at minimum drag speed is 2400 N, the maximum lift-to-drag ratio $(L/D)_{\max}$ of the aircraft is _________ (round off to 1 decimal place).

Subtopic: Drag Polar & Aircraft Performance Equations

An aircraft is to be designed to ensure that it has enough excess power for climb. If the engine produces 500 kW of power and the power required for steady level flight at speed $V$ is 350 kW for an aircraft weight of 12.5 kN, the maximum rate of climb (in m/s) at this speed is _________ (round off to 1 decimal place).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

During an aircraft cruising flight, the altitude above the ground is usually measured using

Subtopic: Climb, Glide, Ceiling & Turn Performance

The load factor of an aircraft turnin g at a constant altitude is 2. The coefficient of lift required for turning flight as compared to level flight at the same speed will be

Subtopic: Range and Endurance of Jet & Propeller Aircraft

A substance experiences an entropy change of 0 s in a quasi-steady process. The rise in temperature (corresponding to the entropy change s ) is highest for the following process:

Subtopic: Climb, Glide, Ceiling & Turn Performance

An aircraft weighing 10000 N is flying level at 100 m/s and it is powered by a jet engine. The thrust required for level flight is 1000 N. The maximum possible thrust produced by the jet engine is 5000 N. The minimum time required to climb 1000 m, when flight speed is 100 m/s, is ________s.

Subtopic: Range and Endurance of Jet & Propeller Aircraft

A glider weighing 3300 N is flying at 1000 m above sea level. The wing area is 14.1 m2 and the air density is 1.23 kg/m^3. Under zero wind conditions, the velocity for maximum range is __________ m/s. $\alpha$ (deg) C L CD C L/CD 11 1.46 0.0865 16.9 9 1.36 0.0675 20.1 7 1.23 0.0535 22.9 5 1.08 0.0440 24.5 3 0.90 0.0350 25.7 1 0.70 0.0275 25.4 -1 0.49 0.0220 22.2 -3 0.25 0.0180 13.8

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Compressors and Turbines (Centrifugal Compressors). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Rocket Propulsion (Solid, Liquid & Hybrid Rocket Engines). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Compressors and Turbines (Axial Flow Gas Turbines & Blade Cooling). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Strength of Materials & Elasticity (Euler Buckling of Columns & Energy Methods). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Structural Dynamics & Aeroelasticity (Free & Forced Vibrations of Continuous Beams). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Standard Atmosphere Properties

Consider the density and altitude at the base of an isothermal layer in the standard atmosphere to be $\rho_1$ and $h_1$, respectively. The density $\rho$ at altitude $h$ ($h > h_1$) in this isothermal layer is given by:

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Thermodynamic Cycles of Gas Turbines (Turbojet, Turbofan & Turboprop Engine Performance). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Strength of Materials & Elasticity (Stress and Strain Tensors & Generalized Hooke's Law). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Strength of Materials & Elasticity (Airframe Structural Analysis & Trusses). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Calculus (Multiple Integrals & Vector Calculus). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Thermodynamic Cycles of Gas Turbines (Thrust Equations & Specific Fuel Consumption). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Compressors and Turbines (Centrifugal Compressors). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Inlets, Combustors & Nozzles (Combustor Design & Flame Stabilization). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Rocket Propulsion (Solid, Liquid & Hybrid Rocket Engines). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Compressors and Turbines (Axial Flow Gas Turbines & Blade Cooling). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Strength of Materials & Elasticity (Euler Buckling of Columns & Energy Methods). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Thin-Walled Structures (Tension Field Beams & Wagner Beams). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Structural Dynamics & Aeroelasticity (Free & Forced Vibrations of Continuous Beams). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Aerospace Materials & Fatigue (Aluminum, Titanium & Aerospace Alloys). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Aerospace Materials & Fatigue (Damage Tolerance & Non-Destructive Testing). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Standard Atmosphere Properties

The moment coefficient measured about the centre of gravity and about aerodynamic centre of a given wing-body combination are 0.0065 and -0.0235 respectively. The aerodynamic centre lies 0.06 chord lengths ahead of the centre of gravity. The lift coefficient for this wing-body is _____.

Subtopic: Climb, Glide, Ceiling & Turn Performance

The vertical ground load factor on a stationary aircraft parked in its hangar is:

Subtopic: Climb, Glide, Ceiling & Turn Performance

Under what conditionshould a glider be operated to ensure minimum sink rate?

Subtopic: Climb, Glide, Ceiling & Turn Performance

For a given airplane with a given wing loading executing a turn in the vertical plane, under what conditions will the turn radius be minimum and the turn rate be maximum?

Subtopic: Climb, Glide, Ceiling & Turn Performance

Data for a light, single-engine, propeller driven aircraft in steady level flight at sea-level is as follows: velocity V∞ = 40m/s, weight W = 13000N, lift coefficient CL = 0.65, drag coefficient CD = 0.025 + 0.04CL 2 and power available Pav = 100,000J/s. The rate of climb possible for this aircraft under the given conditions (in m/s) is

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Compressors and Turbines (Centrifugal Compressors). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Inlets, Combustors & Nozzles (Combustor Design & Flame Stabilization). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Rocket Propulsion (Solid, Liquid & Hybrid Rocket Engines). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Range and Endurance of Jet & Propeller Aircraft

An aerospace system operating under standard sea level conditions is governed by Thin-Walled Structures (Tension Field Beams & Wagner Beams). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Climb, Glide, Ceiling & Turn Performance

Which one of the following criteria leads to maximum turn rate and minimum radius in a level turn flight?

Subtopic: Climb, Glide, Ceiling & Turn Performance

Stall speed of the airplane in m/s is

Subtopic: Climb, Glide, Ceiling & Turn Performance

During the ground roll manoeuvre of an aircraft, the force(s) acting on it parallel to the direction of motion

Subtopic: Climb, Glide, Ceiling & Turn Performance

An aircraft in a steady climb suddenly experiences a 10% drop in thrust. After a new equilibrium is reached at the same speed, the new rate of climb is

Subtopic: Climb, Glide, Ceiling & Turn Performance

The ratio of flight speed to the exhaust velocity for maximum propulsion efficiency is

Subtopic: Climb, Glide, Ceiling & Turn Performance

An aircraft has a steady rate of climb of 300 m/s at sea level and 150 m/s at 2500 m altitude. The time taken (in sec) for this aircraft to climb from 500 m altitude to 3000 m altitude is ____.

Subtopic: Range and Endurance of Jet & Propeller Aircraft

If an aircraft takes off with 10% less fuel in comparison to its standard configuration, its range is

Subtopic: Range and Endurance of Jet & Propeller Aircraft

A vortex flowmeter works on the principle that the Strouhal number of 0.2 is a constant over a wide range of flow rates. If the bluff-body diameter in the flowmeter is 20 mm and the piezo-electric transducer registers the vortex shedding frequency to be 10 Hz, then the velocity of the flow would be measured as

Subtopic: Range and Endurance of Jet & Propeller Aircraft

The maximum distance that th e centre of gravity can be behind aerodynamic centre without destabilizing the wing-tail combination is

Subtopic: Drag Polar & Aircraft Performance Equations

If the mass flow rate is 1 kg/s, the power required to drive the compressor is

Subtopic: Climb, Glide, Ceiling & Turn Performance

In an un-powered glide of an aircraft having weight W, lift L and drag D, the equilibrium glide angle is defined as

Subtopic: Climb, Glide, Ceiling & Turn Performance

In an un-powered glide of an aircraft having weight W, lift L and drag D, the equilibrium glide angle is defined as:

Subtopic: Climb, Glide, Ceiling & Turn Performance

Lift on an aircraft climbing vertically up is:

Subtopic: Drag Polar & Aircraft Performance Equations

It is seen that the drag polar of a certain aerofoil is symmetric about the C_d axis. This drag polar could refer to:

Subtopic: Climb, Glide, Ceiling & Turn Performance

The stall speed of an airplane in steady level flight at sea level is V_s0. At an altitude where the density ratio is sigma = 0.25, the true stall speed is:

Subtopic: Climb, Glide, Ceiling & Turn Performance

For an airplane in level turn at bank angle phi, the load factor n is given by:

Subtopic: Climb, Glide, Ceiling & Turn Performance

AE 2011 AEROSPACE ENGINEERING - AE An aircraft with a mass of 5000 kg takes off from sea level with a forward speed of 50 m/s and starts to climb with a climb angle of 15o. The rate of climb and excess thrust available at the start of the climb respectively (assume g = 9.81 ms-2) are (A) 13.40 m/s and 13146.0 N (B) 12.94 m/s and 12694.1 N

Subtopic: Drag Polar & Aircraft Performance Equations

If 137 + 276 = 435 how much is 731 + 6727

Subtopic: Range and Endurance of Jet & Propeller Aircraft

§ skilled workers can build a wall in 20 days; 8 semi-skilled workers can build a wall in 25 days; 10 unskilled workers can build a wall in 30 days. If a team has 2 skilled, & semi-skilled and 5 unskilled workers, how long will it take to build the wall?

Subtopic: Climb, Glide, Ceiling & Turn Performance

A is the angle of attack, then dC mcG is da

Subtopic: Climb, Glide, Ceiling & Turn Performance

Isp = 200 seconds, the thrust produced by the motor is approximately

Subtopic: Climb, Glide, Ceiling & Turn Performance

Due to this pitching, the horizontal tail surface located 4 metres behind the centre-of-mass of the airplane will experience a change in angle of attack, which is

Subtopic: Climb, Glide, Ceiling & Turn Performance

The contribution of the tail to the aircraft longitudinal stability

Subtopic: Standard Atmosphere Properties

The velocity vector of an aircraft along its body-fixed axis is given by V = If V is the magnitude W of V, a is the angle of attack and B is the angle of sideslip, which of the following set of relations is correct ?

Subtopic: Climb, Glide, Ceiling & Turn Performance

An aircraft of mass 2500 kg in straight and level flight at a constant speed of 100 m/s has available excess power of 1.0 x 10° W. The steady rate of climb it can attain at that speed is

Subtopic: Climb, Glide, Ceiling & Turn Performance

0.025 m 0.025 m chord line 1 cm? 1 cm' 0.5 m The wing root bending moment in steady level flight is M, = 10 N-m. If the airplane flies at a load factor n = 3.5, the maximum bending stress at the root is

Subtopic: Standard Atmosphere Properties

Suppose the non-constant functions F(x) and G(t) satisfy d'F dr + p'F= 0, dG dt +c p'G=0, where p and c are constants. Then the function u(x,t) = F(x)G(t) definitely satisfies d'u

Subtopic: Climb, Glide, Ceiling & Turn Performance

The function f(x) = x^2 - -5x+6

Subtopic: Standard Atmosphere Properties

Which of the following statements is TRUE as the altitude increases in stratosphere of International Standard Atmosphere?

Subtopic: Climb, Glide, Ceiling & Turn Performance

V-n diagram, what is the minimum speed at which it should be designed to withstand the maximum vertical load factor of 9?

Subtopic: Range and Endurance of Jet & Propeller Aircraft

To maximize range of a jet engine aircraft, it should be flown at a velocity that maximizes

Subtopic: Drag Polar & Aircraft Performance Equations

If the slip factor is 0.85, the relative velocity at the blade tip is

Subtopic: Drag Polar & Aircraft Performance Equations

The thrust required for steady level flight will be minimum when the aircraft operates at a lift coefficient of

Subtopic: Range and Endurance of Jet & Propeller Aircraft

The glide angle that results in maximum range in a power-off glide is

Subtopic: Climb, Glide, Ceiling & Turn Performance

A spring-mass-damper system is excited by a force F, sinct. The amplitude at resonance is measured to be 1 cm. At half the resonant frequency, the amplitude is 0.5 cm. The damping ratio of the system is

Subtopic: Drag Polar & Aircraft Performance Equations

Relative to the forward stagnation point, the angular positions along the circumference where the speed along the surface of the cylinder is equal to the free stream speed are

Subtopic: Climb, Glide, Ceiling & Turn Performance

V (True air speed) The maximum rate of climb achievable by this airplane at 5 km altitude will be

Subtopic: Climb, Glide, Ceiling & Turn Performance

If during the maximum rate of climb at 5 km altitude, the airplane was flying at an angle of attack of 4 degrees and attitude (pitch) angle of 5 degrees, what was equivalent airspeed of the airplane?