Download GTU BE/B.Tech 2019 Winter 5th Sem New 2150101 Flight Mechanics Question Paper

Download GTU (Gujarat Technological University) BE/BTech (Bachelor of Engineering / Bachelor of Technology) 2019 Winter 5th Sem New 2150101 Flight Mechanics Previous Question Paper

1
Seat No.: ________ Enrolment No.___________

GUJARAT TECHNOLOGICAL UNIVERSITY

BE - SEMESTER ? V (New) EXAMINATION ? WINTER 2019
Subject Code: 2150101 Date: 25/11/2019

Subject Name: Flight Mechanics
Time: 10:30 AM TO 01:00 PM Total Marks: 70

Instructions:
1. Attempt all questions.
2. Make suitable assumptions wherever necessary.
3. Figures to the right indicate full marks.


MARKS

Q.1 (a) Define: Pressure, Temperature and Density altitudes. 03
(b) Explain Attached flow and Separated flow with an example. 04
(c) Write a note on International Standard Atmosphere. 07


Q.2 (a) Explain Prandtl-Glauert rule. 03
(b) Compare lift curves for symmetric and cambered airfoils with explanation. 04
(c) Explain Critical Mach number. Show the effect of airfoil thickness on critical
Mach number.
07
OR
(c) List down different types of drag. Explain wave drag in detail. 07
Q.3 (a) Identify the performance of finite and infinite wings. 03
(b) Relate the zero-lift drag and induced drag for minimum thrust requirement
condition.
04
(c) Derive expressions for Range and Endurance for jet airplane. 07
OR
Q.3 (a) Define: Range, Endurance, Wing Loading 03
(b) Explain Absolute and Service Ceilings. 04
(c) Explain V-n diagram with neat sketch. 07
Q.4 (a) Define: Aspect Ratio, Pressure Coefficient, Induced drag. 03
(b) Demonstrate the effect of altitude on power required and power available. 04
(c) Estimate the Landing ground roll distance at sea level for the aircraft having
empty weight of 54966 kg. No thrust reversal is used; However, spoilers are
operated such that L=0. The maximum lift coefficient (CL max) with fully flaps
employed at touch down is 2.5. Wing area is 29.54 m
2
.CD,0 = 0.022 & ?r=0.4.
07
OR
Q.4 (a) Derive Hydrostatic equation. 03
(b) Contrast Stick fixed stability and Stick free stability. 04
(c) Make use of Newton?s 2
nd
law to derive the equation of motion for level
unaccelerated flight.
07
Q.5 (a) Define and explain Elevator angle to trim the airplane to desired angle. 03
(b) Explain Static margin. 04
(c) Explain Longitudinal static stability in detail. 07
OR

Q.5 (a) Define Static Stability and Dynamic Stability. 03
(b) Define Neutral point. Show that it is a crucial parameter for longitudinal static
stability.
04
(c) Classify different types of Flaps. 07
*************

FirstRanker.com - FirstRanker's Choice