# GATE AE Question Paper 2008 Aerospace Engineering

GATE AE Question Paper 2008 Aerospace Engineering.

GATE i.e. Graduate Aptitude Test in Engineering Aerospace Engineering 2008 Exam Has been Conducted by IISc Bangalore IIT Bombay IIT Delhi IIT Guwahati IIT Kanpur IIT Kharagpur IIT Madras IIT Roorkee. This GATE AE 2008 examination is the procedure to get the admission in M.Tech

GATE Aerospace Engineering i.e. AE Question Paper, This GATE AE 2008 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 2008 question paper in pdf file for GATE AE you can download it in FRAE, if GATE Aerospace Engineering 2008 paper in text for GATE AE you can download GATE AE 2008 page also just Go to menu bar, Click on File->then Save.

## GATE AE Question Paper 2008 Aerospace Engineering

GATE AE 2008 Question paper Free Download PDF is available in www.oldquestionpapers.net which has been provided by many students this GATE Aerospace Engineering 2008 paper is available for all the students in FRAE and also GATE AE 2008 question paper fully solved i.e with answer keys and solution.

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Q.4 To transfer a satellite from an elliptical orbit to a circular orbit having radius equal to the apogee
distance of the efliptical orbit, the speed of the satellite should be
(A) increased at the apogee
(B) decreased at the apogee
(C) increased at the perigee
(D) decreased at the perigee

Q.5 The service ceiling of a transport aircraft is defined as the altitude
(A) that is halfway between sea-level and absolute ceiling
(B) at which it can cruise with one engine operational
(C) at which its maximum rate of climb is zero
(D) at which its maximum rate of climb is 0.508 mIs

Q.6 The drag of an aircraft in steady climbing flight at a given forward speed is
(A) inversely proportional to climb angle
(B) higher than drag in steady level flight at the same tbrward speed
(C) lower than drag in steady level flight at the same forward speed
(D) independent of climb angle

Q.8 The parameters that remain constant in a cruise-climb of an aircraft are
(A) equivalent airspeed and lift coeflicient (B) altitude and lift coefficient
(C) equivalent airspccd and altitude (D) lift coefficient and aircraft mass

Q.9 The maximum thickness to chord ratio for the NACA 24012 airfoil is
(A)0.0l (B) 0.12 (C)O.24 (D)O.40

Q. 10 The maximum possible value of pressure coefficient C, in incompressible flow is
(A)0.5 (11)1 (C)it (D)co

Q. 11 An irrotarional and inviscid flow can become rotational on passing through a
(A) normal shock wave (B) oblique shock wave
(C) curved shock wave (D) Mach wave

Q. 12 Laminar flow airfoils are used to reduce
(A) trim drag (B) skin friction drag
(C) induced drag (D) wave drag