GUJARAT TECHNOLOGICAL UNIVERSITY
BE - SEMESTER-V (NEW) EXAMINATION - WINTER 2018
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Subject Code:2150107 Date:04/12/2018
Subject Name:Aerodynamics I
Time: 10:30 AM TO 01:00 PM Total Marks: 70
Instructions:
- Attempt all questions.
- Make suitable assumptions wherever necessary.
- Figures to the right indicate full marks.
- Usage of Isentropic properties table and Normal Shock properties table are permitted
- Usage of @ — f — M chart is permitted
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MARKS
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Q.1 (a) Explain different types of elementary flows. 03
(b) What is Aerodynamics? Write an application of Aerodynamics in the 04 various fields.
(c) Explain with neat sketches the forces and moments acting on an aircraft. 07
Q.2 (a) Write short note on airfoil stalling. 03
(b) Classify the NACA series standard for airfoils with a neat sketch. 04
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(c) For a particular aerofoil section the pitching moment coefficient about 07 an axis 1/3 chord behind the leading edge varies with the lift coefficient in the following manner:
CL 0.2 0.4 0:6 0.8
Cm -0.02 0.00 +0.02 +0.04
Find the aerodynamic centre and the value of Cmo
OR
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(c) Consider the lifting over a circular cylinder. The list coefficient is 5. 07 Calculate the peak (negative) pressure coefficient.
Q.3 (a) Enlist various types of drags on an airfoil. 03
(b) Draw and explain‘coefficient of lift V/s angle of attack for cambered airfoil. 04
(c) What is airfoil? Explain characteristics of airfoil with a neat sketch. 07
OR
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Q.3 (a) Define: Source flow, Doublet , Principle of Superposition 03
(b) Explain detached shock wave in front of a blunt body. 04
(c) Consider an NACA 2412 airfoil with a chord of 0.64 m in an airstream 07 at standard sea level conditions (p = 1.23 kg/m³). The free stream velocity is 70 m/s. the lift per unit span is 1254 N/m. Calculate
a. The angle of attack
b. Drag per unit span.
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c. The moment per unit span about the aerodynamic center.
Q.4 (a) Write a note on vorticity and circulation. 03
(b) Show that free vortex is an example of irrotational motion. 04
(c) Write a note on Rankine Oval Body. 07
Q4 (a) Write a short note on Normal Shock wave. 03
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(b) Derive an equation of speed of sound. 04
(c) Consider a point in an air flow where the local Mach number, static 07 pressure and static temperature are 3.5, 0.3 atm and 180 K respectively. Calculate the local values of po, To, T, a* and M*.
Q.5 (a) What is the function of Pitot Tube? How is it work? 03
(b) Derive an equation for Stream function and Velocity potential for a uniform flow. 04
(c) Consider a normal shock wave in air where the upstream flow 07 properties are u; = 680 m/s, T1 = 288 K, and p; = 1 atm. Calculate the velocity, temperature, and pressure downstream of the shock.
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OR
Q.5 (a) What is Shock? What happens to the flow properties during the shock? Explain in brief. 03
(b) With a neat sketch explain lifting flow over circular cylinder. 04
(c) Consider a supersonic flow with M =2, p=1 atm and T = 288 K. This 07 flow is detected at a compression corner through 20 °. Calculate M, p, T, po and To behind the resulting oblique shock wave.
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