Download GTU BE/B.Tech 2019 Summer 8th Sem New 2180105 High Speed Aerodynamics Question Paper

Download GTU (Gujarat Technological University) BE/BTech (Bachelor of Engineering / Bachelor of Technology) 2019 Summer 8th Sem New 2180105 High Speed Aerodynamics Previous Question Paper

Seat No.: ________ Enrolment No.___________

GUJARAT TECHNOLOGICAL UNIVERSITY

BE - SEMESTER ?VIII(NEW) EXAMINATION ? SUMMER 2019
Subject Code: 2180105 Date:13/05/2019

Subject Name: High Speed Aerodynamics

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.

Q.1 (a) Define Hypersonic flow in technical language. 03
(b)
What is the difference between aerothermodynamics and
aerodynamics?
04
(c)
Explain construction of subsonic open type wind tunnel with neat
sketch.
07

Q.2 (a) Prove Cp=2sin
2
? for Newtonian theory. 03
(b)
Consider an infinitely thin flat plate at an angle of attack of 15
0
in a
mach 8 flow. Calculate lift to drag ratio.
04
(c) Explain Solid blockage and wake blockage. 07
OR
(c)
Explain Centrifugal force corrections to Newtonian theory with neat
sketch.
07
Q.3 (a) Define wind tunnel balances. 03
(b)
Air is travelled over the object with 12 Mach flow and shock angle is
2
0
(?) free stream pressure consider 101325 pa. Estimate downstream
pressure (P2).
04
(c) Prove L/D = Cot? 07
OR
Q.3 (a) List out flow visualization techniques. 03
(b) What is the difference between supersonic and hypersonic wind tunnel? 04
(c)
Explain ?-?-M diagram with neat sketch and prove
?Hypersonic limit for a slender wedge, the wave angle is only 20%
larger than the wedge angle?.
07
Q.4 (a) What is Tangent cone method? 03
(b) Explain Shock expansion method. 04
(c) Explain Aerodynamic heating. 07
OR
Q.4 (a) With neat sketch explain thin shock layer. 03
(b) Define and explain entropy layer. 04
(c)
An object immersed in airflow is described as follows
Static pressure = 200 Kpa, Static Temperature = 293 K, Velocity of
flow is 250m/s, Estimate stagnation temperature and stagnation
pressure.
07
Q.5 (a) Define ?High temperature flow? characteristic for hypersonic flow. 03
(b) Explain Low density flow. 04
(c)
Consider a flat plate at a 5
0
angle of attack in a mach 2.2 flow. Using
prandtl meyer functions find out exit mach number. Take gama(?) = 1.4
07
OR

Q.5 (a) Explain flow over an airfoil case for hypersonic case. 03
(b) Difference between supersonic flow and hypersonic flow. 04
(c) Why car is not fly at Subsoinc, Supersoinc and hypersonic speed? 07

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