Download PTU B.Tech 2020 March Aero 5th Sem ANE 312 Aerodynamics ? Ii Question Paper

Download PTU (I.K. Gujral Punjab Technical University Jalandhar (IKGPTU) ) BE/BTech Aero (Aerospace-Engg) 2020 March 5th Sem ANE 312 Aerodynamics ? Ii Previous Question Paper

1 | M-60521 (S2)-1034
Roll No. Total No. of Pages : 02
Total No. of Questions : 09
B.Tech.(ANE) (Sem.?5)
AERODYNAMICS ? II
Subject Code : ANE-312
M.Code : 60521
Time : 3 Hrs. Max. Marks : 60
INSTRUCTIONS TO CANDIDATES :
1. SECTION-A is COMPULSORY consisting of TEN questions carrying TWO marks
each.
2. SECTION-B contains FIVE questions carrying FIVE marks each and students
have to attempt any FOUR questions.
3. SECTION-C contains THREE questions carrying TEN marks each and students
have to attempt any TWO questions.

SECTION-A
Q1. Attempt the following :
a) Define Kutta condition.
b) Draw lift curves for symmetrical and cambered airfoil sections.
c) What do you mean by formation flying?
d) Distinguish between upwash and downwash.
e) Define induced drag.
f) Define Critical Mach number.
g) Define supersonic and subsonic leading edges.
h) Define supercritical airfoils.
i) What do you mean by HAA aerodynamics?
j) Define Conformal transformations.

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1 | M-60521 (S2)-1034
Roll No. Total No. of Pages : 02
Total No. of Questions : 09
B.Tech.(ANE) (Sem.?5)
AERODYNAMICS ? II
Subject Code : ANE-312
M.Code : 60521
Time : 3 Hrs. Max. Marks : 60
INSTRUCTIONS TO CANDIDATES :
1. SECTION-A is COMPULSORY consisting of TEN questions carrying TWO marks
each.
2. SECTION-B contains FIVE questions carrying FIVE marks each and students
have to attempt any FOUR questions.
3. SECTION-C contains THREE questions carrying TEN marks each and students
have to attempt any TWO questions.

SECTION-A
Q1. Attempt the following :
a) Define Kutta condition.
b) Draw lift curves for symmetrical and cambered airfoil sections.
c) What do you mean by formation flying?
d) Distinguish between upwash and downwash.
e) Define induced drag.
f) Define Critical Mach number.
g) Define supersonic and subsonic leading edges.
h) Define supercritical airfoils.
i) What do you mean by HAA aerodynamics?
j) Define Conformal transformations.

2 | M-60521 (S2)-1034
SECTION-B
Q2 Explain the complete vortex system.
Q3 Consider a finite wing with an aspect ratio of 8 and a taper ratio of 0.8. The airfoil section
is thin and symmetric. Assume that ? = ? = 0.055. Calculate the lift coefficient and
induced drag coefficients for this wing at a geometric angle of attack of 5?.
Q4 Explain Prandtl?s classical lifting line theory.
Q5 Explain the Helmholtz?s theorems of vortex motion.
Q6 Write a note on : ?Vortex Panel Method?.

SECTION-C
Q7 Consider an NACA airfoil whose mean camber line is given by :
z/c = 2.6595 [(x/c)
3
? 0.6075 (x/c)
2
+ 0.1147 (x/c)] for 0 ? ?(x/c) ? 0.2025
z/c = 0.02208 [1 ? (x/c)] for 0.2025 ? (x/c) ?1
Calculate :
a) The angle of attack at zero lift (8)
b) The lift coefficient when ? = 6? (2)
Q8 Write notes on the following :
a) Prandtl - Glauert compressibility correction. (5)
b) Leading edge suction analogy. (5)
Q9 Define Kutta-Juokowaski transformation and use it to transform a circle into a cambered
airfoil. Calculate the theoretical lift coefficient of a Zhukovsky airfoil having thickness
ratio of 0.2 and camber of 3%, set at 3? incidence in a two dimensional irrotational flow.
(2, 5, 3)

NOTE : Disclosure of Identity by writing Mobile No. or Making of passing request on any
page of Answer Sheet will lead to UMC against the Student.
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