Download GTU BE/B.Tech 2019 Summer 6th Sem New 2160101 Aerodynamics Ii Question Paper

Download GTU (Gujarat Technological University) BE/BTech (Bachelor of Engineering / Bachelor of Technology) 2019 Summer 6th Sem New 2160101 Aerodynamics Ii Previous Question Paper

1
Seat No.: ________ Enrolment No.___________

GUJARAT TECHNOLOGICAL UNIVERSITY
BE - SEMESTER ? VI(NEW) ? EXAMINATION ? SUMMER 2019
Subject Code: 2160101 Date: 10/05/2019
Subject Name: Aerodynamics II
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) Plot Variation of CL with Re, and aspect ratio. 03
(b) Define mean aerodynamic chord [MAC] and procedure to find
MAC.
04
(c) Derive expression for classical thin airfoil theory. 07

Q.2 (a) Define:- Turbulent flow, Transition and dihedral. 03
(b) State Kelvin Circulation Theorem. 04
(c) Explain The Vortex lattice method. 07
OR
(c) Explain Kutta-Joukowsky Transformation and details procedure
about transformation of circle into symmetric airfoil.
07
Q.3 (a) Write Kutta Condition and explain with sketch. 03
(b) Differentiate between finite and infinite wing. Derive expression
for ?a? (CL-? slope) and ?a0.?
04
(c) What is Transformation? Explain transformation of a circle into a
straight line with a neat sketch.
07
OR
Q.3 (a) What is bound vortex and Horse shoe vortex? 03
(b) Explain Numerical Nonlinear Lifting Line Method 04
(c) Explain Prandtle lifting line theory and derive expression for
downwash velocity.
07
Q.4 (a) Explain Prandtl-Glauert Compressibility correction, 03
(b) Explain formation of primary and secondary vortex on delta wing. 04
(c) Derive Linearised Supersonic Pressure Coefficient formula. 07
OR
Q.4 (a) Explain the area rule with neat sketch. 03
(b) At a given point on the surface of an airfoil, the pressure
coefficient is -0.3 at very low speeds. If the free stream Mach
Number is 0.6. Calculate Cp at this point.
04
(c) Derive expression for induced velocity by finite and infinite
,vortex tube
07
Q.5 (a) What is whitcomb airfoil 03
(b) A straight finite wing has aspect ratio 8 operating at angle of
attack 4
0
.calculate CDi (induced drag coefficient) and CL assume
that wing identical to flat plate
04
(c) Using KJT transform cylinder into symmetrical airfoil 07


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1
Seat No.: ________ Enrolment No.___________

GUJARAT TECHNOLOGICAL UNIVERSITY
BE - SEMESTER ? VI(NEW) ? EXAMINATION ? SUMMER 2019
Subject Code: 2160101 Date: 10/05/2019
Subject Name: Aerodynamics II
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) Plot Variation of CL with Re, and aspect ratio. 03
(b) Define mean aerodynamic chord [MAC] and procedure to find
MAC.
04
(c) Derive expression for classical thin airfoil theory. 07

Q.2 (a) Define:- Turbulent flow, Transition and dihedral. 03
(b) State Kelvin Circulation Theorem. 04
(c) Explain The Vortex lattice method. 07
OR
(c) Explain Kutta-Joukowsky Transformation and details procedure
about transformation of circle into symmetric airfoil.
07
Q.3 (a) Write Kutta Condition and explain with sketch. 03
(b) Differentiate between finite and infinite wing. Derive expression
for ?a? (CL-? slope) and ?a0.?
04
(c) What is Transformation? Explain transformation of a circle into a
straight line with a neat sketch.
07
OR
Q.3 (a) What is bound vortex and Horse shoe vortex? 03
(b) Explain Numerical Nonlinear Lifting Line Method 04
(c) Explain Prandtle lifting line theory and derive expression for
downwash velocity.
07
Q.4 (a) Explain Prandtl-Glauert Compressibility correction, 03
(b) Explain formation of primary and secondary vortex on delta wing. 04
(c) Derive Linearised Supersonic Pressure Coefficient formula. 07
OR
Q.4 (a) Explain the area rule with neat sketch. 03
(b) At a given point on the surface of an airfoil, the pressure
coefficient is -0.3 at very low speeds. If the free stream Mach
Number is 0.6. Calculate Cp at this point.
04
(c) Derive expression for induced velocity by finite and infinite
,vortex tube
07
Q.5 (a) What is whitcomb airfoil 03
(b) A straight finite wing has aspect ratio 8 operating at angle of
attack 4
0
.calculate CDi (induced drag coefficient) and CL assume
that wing identical to flat plate
04
(c) Using KJT transform cylinder into symmetrical airfoil 07


2

OR
Q.5 (a) State Helmholtz?s theorem 03
(b) Consider flow over the NACA 2412 airfoil where Rex 3240000.
Calculate the boundary layer thickness at 1.5 m from leading edge
04
(c) Define Critical Mach number and Drag Divergence Mach
Number? Explain both the terms in detail with a proper diagram.
07


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