GATE AE 2009 Question Paper & Solutions

Quantitative Aptitude

For two-dimensional irrotational and incompressible flows

Quantitative Aptitude

A trailing edge plain flap deflected downward increases the lift coefficient of an airfoil by

Quantitative Aptitude

The ordinary differential equation ds? + ky = 0 where k is real and positive

Quantitative Aptitude

A non-trivial solution to the (nXn) system of equations [A]{x} = {0}, where {0} is the null vector

Quantitative Aptitude

The propulsive efficiency of a turbo-jet engine moving at velocity Uo and having exhaust velocity Ue with respect to the engine is given by

Quantitative Aptitude

An aircraft is flying at M = 2 where the ambient temperature around the aircraft is 250 K. If the specific heat ratio for air y = 1.4, the stagnation temperature on the surface of the aircraft is

Quantitative Aptitude

The division of feed air to an aircraft gas-turbine combustor into primary and secondary streams serves which of the following purposes ? P. a flammable mixture can be formed Q. cooling of combustor liner and flame tube can be accomplished R. specific fuel consumption can be reduced

Quantitative Aptitude

The propulsive efficiency of a turbo-jet engine moving at velocity U_inf and having exhaust velocity U_e with respect to the engine is given by:

Quantitative Aptitude

An unswept fixed-winged aircraft has a large roll stability if the wing is placed

Quantitative Aptitude

Thrust available from a turbojet engine

Atmospheric Flight Mechanics

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

Space Dynamics & Orbital Mechanics

The life of a geo-stationary communications satellite is limited by

Calculus

For a critically damped single degree of freedom spring - mass - damper system with a damping constant c of 4 Ns/m and spring constant k of 16 N/m, the system mass m is

Inlets, Combustors & Nozzles

An ideal axial compressor is driven by an ideal turbine across which the total temperature ratio is 0.667. If the total temperature at turbine inlet is To = 1500 K and specific heat of gas c, = 1 kJ/kg/K, the power drawn by the compressor per unit mass flow rate of air is approximately

Rocket Propulsion

The performance of a solid rocket motor is improved by replacing the old propellant with a new one. The new propellant gives a combustion temperature 40% higher than the previous propellant without appreciable change in molecular weight of combustion products and other operating parameters. By approximately what percentage is the specific impulse of the new motor higher than the old one ?

Atmospheric Flight Mechanics

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

Inlets, Combustors & Nozzles

When the afterburner is turned on, (assuming the total pressure remains the same, the mass of fuel added in the afterburner is negligible i.e., the mass flow rate remains the same, and the specific heat ratio (Y) remains constant), approximately by what factor must the nozzle area be changed ?

Atmospheric Flight Mechanics

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

Atmospheric Flight Mechanics

The contribution of the tail to the aircraft longitudinal stability

Linear Algebra

The linearized dynamics of an aircraft (which has no large rotating components) in straight and level flight is governed by the equations dx dt [[a] [в]]. [[c] [D] where x=[u w q 0 v pr ], [I represents the transpose of a matrix, [A], [B], [C] and [D] are 4x4 matrices and [O] is the 4x4 null matrix. Which of the following is true ?

Atmospheric Flight Mechanics

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 ?

Atmospheric Flight Mechanics

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

Space Dynamics & Orbital Mechanics

Mars to the escape velocity from the surface of earth is approximately

Dynamic Stability

Stagnation temperature increases.

Airfoil & Wing Theory

A model airfoil in a wind tunnel that is operating at 50 m/s develops a minimum pressure co-efficient of - 6.29 at some point on its upper surface. The local airspeed at that point is

Airfoil & Wing Theory

A symmetrical airfoil section produces a lift coefficient of 0.53 at an angle of attack of 5 degrees measured from its chord line. An untwisted wing of elliptical planform and aspect ratio 6 is made of this airfoil. At an angle of attack of 5 degrees relative to its chordal plane, this wing would produce a lift coefficient of

Compressors and Turbines

d Which of the following statements is true ?

Basic Fluid Mechanics

If the free stream speed is increased by 50%, then the new boundary layer thickness at this location will be approximately

Strength of Materials & Elasticity

The buckling load for a simply supported column of rectangular cross section of dimensions 1 cmx1.5 cm and length 0.5 m made of steel (E = 210x10% N/m') is approximately

Atmospheric Flight Mechanics

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

Thin-Walled Structures

The torque balance equation (Bredt-Batho formula) for this section leads to

Numerical Methods

2009 AE The value of the integral 1+ x + sin x - evaluated using the trapezoidal rule with two equal intervals is approximately

Basic Fluid Mechanics

In an aerospace engineering analysis of Thin-Walled Structures (Shear Flow in Open and Closed Thin-Walled Beams), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Linear Algebra

The pair of eigenvalues that represent the phugoid mode is

Dynamic Stability

The short period damped frequency is

Linear Algebra

A normal to the surface is

Basic Fluid Mechanics

If the sensible enthalpy of fuel is neglected, the temperature of combustion products from the reaction of primary air stream with fuel is approximately

Inlets, Combustors & Nozzles

The approximate ratio of mass flow rates of the primary air stream to the secondary air stream required to achieve the turbine inlet total temperature of 1550 K is:

Differential Equations

After 10 seconds, the change in specific internal energy of the air is

Airfoil & Wing Theory

J/kg-K respectively, the corresponding change in the temperature of the air is

Basic Fluid Mechanics

In an aerospace engineering analysis of Basic Fluid Mechanics (Viscous Flow & Boundary Layer Equations), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Compressible Flow & Shocks

In an aerospace engineering analysis of Compressible Flow & Shocks (Normal & Oblique Shock Waves), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Airfoil & Wing Theory

In an aerospace engineering analysis of Airfoil & Wing Theory (Finite Wing Theory & Induced Drag), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Compressible Flow & Shocks

In an aerospace engineering analysis of Compressible Flow & Shocks (Rayleigh & Fanno Flow), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Basic Fluid Mechanics (Incompressible Potential Flow & Stream Functions), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Airfoil & Wing Theory

In an aerospace engineering analysis of Airfoil & Wing Theory (High-Lift Devices & Flaps), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Atmospheric Flight Mechanics (Drag Polar & Aircraft Performance Equations), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Atmospheric Flight Mechanics (Range and Endurance of Jet & Propeller Aircraft), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Static Stability & Control (Static Margin & Stick-Fixed/Free Stability), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Dynamic Stability (Dutch Roll, Spiral & Roll Subsidence Modes), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Space Dynamics & Orbital Mechanics (Hohmann Transfer & Orbital Maneuvers), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Space Dynamics & Orbital Mechanics (Rocket Trajectory & Staging), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Thermodynamic Cycles of Gas Turbines (Brayton Cycle with Real Component Efficiencies), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Thermodynamic Cycles of Gas Turbines (Thrust Equations & Specific Fuel Consumption), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Inlets, Combustors & Nozzles (Convergent & Convergent-Divergent (C-D) Nozzles), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Compressors and Turbines (Centrifugal Compressors), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Inlets, Combustors & Nozzles (Combustor Design & Flame Stabilization), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Rocket Propulsion (Solid, Liquid & Hybrid Rocket Engines), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Compressors and Turbines (Axial Flow Gas Turbines & Blade Cooling), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Strength of Materials & Elasticity (Euler Buckling of Columns & Energy Methods), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Thin-Walled Structures (Torsion of Multi-Cell Thin-Walled Tubes), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Thin-Walled Structures (Tension Field Beams & Wagner Beams), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Structural Dynamics & Aeroelasticity (Free & Forced Vibrations of Continuous Beams), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Aerospace Materials & Fatigue (Aluminum, Titanium & Aerospace Alloys), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Basic Fluid Mechanics

In an aerospace engineering analysis of Aerospace Materials & Fatigue (Damage Tolerance & Non-Destructive Testing), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?