GUJARAT TECHNOLOGICAL UNIVERSITY
BE - SEMESTER- VI (New) EXAMINATION — WINTER 2019
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Subject Code: 2160101 Date: 04/12/2019Subject Name: Aerodynamics II
Time: 02:30 PM TO 05:00 PM Total Marks: 70
Instructions:
- Attempt all questions.
- Make suitable assumptions wherever necessary.
- Figures to the right indicate full marks.
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Q.1 (a) Define Airfoil. Difference between Airfoil and Wing. 03
(b) With neat sketch explain Airfoil nomenclature. 04
(c) Explain Airfoil characteristics with appropriate graph. 07
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Q.2 (a) Define Vortex filament. 03
(b) Consider NACA 2414 airfoil with a chord of 0.64 m in an 04
airstream at standard sea level conditions. The freestream
velocity is 70 m/s. The lift per unit span is 1254 N/m.
Calculate the co-efficient of lift.
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(c) Derive Linearized velocity potential equations. 07
OR
(c) Prove the relation ‘Local jump in tangential velocity 07
across the vortex sheet is equal to the local sheet strength”
using vortex sheet.
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Q.3 (a) What is the physical phenomena of Vi=Vj in Kutta 03
Condition?.
(b) Without friction could we have Lift?-Explain properly 04
(c) Explain with neat sketch Kelvin’s circulation theorem. 07
OR
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Q.3 (a) Define Downwash and Induced drag. 03
(b) Explain stream function with equations. 04
(c) Prove the relation “Camber line is a streamline of the 07
flow” in thin airfoil theory.
Q.4 (a) Define Biot-Savart Law with equation. 03
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(b) Draw and explain an elliptic lift distribution. 04
(c) Explain with "appropriate equation Prandtl’s Classical 07
Lifting Line theory.
OR
Q.4 (a) Define 1. Aspect ratio 2. Compressible flow 03
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(b) Explain General lift distributions with appropriate 04
equations.
(c) Explain with “Lift Curves for an infinite wing versus a 07
finite elliptic wing”.
Q.5 (a) Difference between subsonic and supersonic flow. 03
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(b) Define Critical Mach number with appropriate equation. 04
(c) Derive Prandtl Glauert Compressibility corrections rule. 07
OR
Q.5 (a) Using Linearized theory, calculate the lift coefficient for a 03
flat plate at a 5° angle of attack in a Mach 3 flow.
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(b) Draw “Linearized supersonic flow over an airfoil”. 04
(c) Derive with neat sketch “Numerical vortex panel method 07
equation”.
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