GATE AE Question Paper 2009 Aerospace Engineering

GATE AE Question Paper 2009 Aerospace Engineering.

GATE i.e. Graduate Aptitude Test in Engineering Aerospace Engineering 2009 Exam Has been Conducted by IISc Bangalore IIT Bombay IIT Delhi IIT Guwahati IIT Kanpur IIT Kharagpur IIT Madras IIT Roorkee. This GATE AE 2009 examination is the procedure to get the admission in M.Tech

GATE Aerospace Engineering i.e. AE Question Paper, This GATE AE 2009 Question will help all the students for their exam preparation, here the question type is MCQ i.e multiple choice question answers, if this GATE AE 2009 question paper in pdf file for GATE AE you can download it in FRAE, if GATE Aerospace Engineering 2009 paper in text for GATE AE you can download GATE AE 2009 page also just Go to menu bar, Click on File->then Save.

GATE AE Question Paper 2009 Aerospace Engineering

GATE AE 2009 Question paper Free Download PDF is available in www.oldquestionpapers.net which has been provided by many students this GATE Aerospace Engineering 2009 paper is available for all the students in FRAE and also GATE AE 2009 question paper fully solved i.e with answer keys and solution.

You can get daily updates on GATE AE 2009 from www.oldquestionpapers.net here you can also check similar links for other related study materials on GATE Aerospace Engineering exam. Here GATE AE 2009 question is also available in English.

Q. 1 For a flow through a Prandtl-Meyer expansion wave
(A) Mach number stays constant. (B) Entropy stays constant.
(C) Temperature stays constant. (D) Density stays constant.

Q.2 For two-dimensional irrotational and incompressible flows
(A) Both potential and stream functions satisfy the Laplace equation.
(B) Potential function must satisfy the Laplace equation but the stream function need not.
(C) Stream function must satisfy the Laplace equation but the potential function need not.
(D) Neither the stream function nor the potential function need to satisfy the Laplace equation.

Q.3 A trailing edge plain flap deflected downward increases the lift coefficient of an airfoil by
(A) Increasing the effective camber of the airfoil.
(B) Delaying the separation of the flow from the airfoil surface.
(C) Increasing the local airspeed near the trailing edge.
(D) Controlling the growth of the boundary layer thickness along the airfoil surface.

Q.9 An aircraft is flying at M = 2 where the ambient temperature around the aircraft ic 250 K. If the
specific heat ratio for air y = 1.4, the stagnation temperature on the surface of the aircraft is
(A)200K (B)450K (C)350K (D)1450K

Q. 10 The division of feed air to an aircraft gas-turbine combustor ino 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
(A) P and R (B) Q and R (C) P and Q (D) P Q and R

Q.12 A conventional altimeter is a
(A) Pressure transducer (B) Temperature transducer
(C) Density transducer (D) Velocity transducer

Q. 14 An unswept fixed-winged aircraft has a large roll stability if the wing is placed
(A) low on the fuselage and has negative dihedral angle
(B) low on the fuselage and has positive dihedral angle
(C) high on the fuselage and has negative dihedral angle
(D) high on the fuselage and has positive dihedral angle

Q.15 Thrust available from a turbojet engine
(A) increases as altitude increases
(B) increases up to the tropopause and then decreases
(C) remains constant at all altitudes
(D) decreases as altitude increases

Click Here Download This Paper