PTU Punjab Technical University B-Tech May 2019 Question Papers 5th Semester Aerospace Engineering
Total No. of Pages :02
Total No. of Questions : 09
B.Tech.(ANE) (Sem.?5)
AIRCRAFT PERFORMANCE
Subject Code : ANE-315
M.Code : 60524
Time : 3 Hrs. Max. Marks : 60
INSTRUCTIONS TO CANDIDATES :
1.
SECTION-A is COMPULSORY consisting of TEN questions carrying T WO marks
each.
2.
SECTION-B contains FIVE questions carrying FIVE marks each and students
have to attempt any FOUR questions.
3.
SECTION-C contains T HREE questions carrying T EN marks each and students
have to attempt any T WO questions.
SECTION-A
Q.1 Distinguish between the following :
(a) `Low Wing loading' and `High wing loading'.
(b) `Range' and `Endurance'.
(c) `Aerodynamic Center' and `Center of Gravity'.
(d) `Geometric altitude' and `Geopotential altitude'.
(e) `Troposphere'' and `Stratosphere'.
(f) `Washin' and `Washout'.
(g) `Camber' and `Camber line'.
(h) `Dihedral angle' and `Anhedral angle'.
(i) `Mach Number' and `Critical Mach number'.
(j) `Skin friction drag' and `Pressure drag'.
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SECTION-B
Q.2 Calculate the standard atmospheric values of T, p and at a geo-potential altitude of
30 km. The values of T, p and at 12 km altitude are 216.66K, 19399Nm?2 and
0.31194 kg-m3 respectively. Assume Lapse rate of + 2.8 K/km above 25km altitude.
Q.3 Explain `Delta Wing Aerodynamics' at Low Speed with the help of labelled
illustration/plots.
Q.4 Derive the expression for lift coefficient, drag coefficient and speed for minimum drag
condition.
Q.5 Define and explain various high lift devices. Show their effect on lift curve slopes.
Q.6 Explain the nomenclature of `4-digit' and `5-digit' NACA series airfoils.
SECTION-C
Q.7 Gulfstream-IV twin turbofan executive transport with weight of 200000N, planform area of
80 m2 and drag polar as C
2
D = 0.015 + 0.08CL is flying at an altitude of 10 km
( = 0.413 kg/m3). Calculate :
(a) Lift coefficient corresponding to (C 3/2
l/2
L
/CD)max, (CL/CD)max, and (CL /CD)max conditions.
(3)
(b) (C 3/2
1/2
L
/CD)max, (CL/CD )max and (CL /CD )max values and their ratio.
(4)
(c) Velocities at which (C 3/2
l/2
L
/CD)max, (CL/CD )max, and (CL /CD )max occur.
(3)
Q.8 Write notes on the following :
(a) Drag, Drag polar, Drag bucket
(6)
(b) V/STOL vehicles
(4)
Q.9 Calculate the total take-off distance at sea level of an aircraft weighing 200000N and also
compare it with the value obtained from approximate relation with the help of following
data (Use calculations at V = 0.7VLO): (Assume CL = 0.1 during ground roll)
(10)
C
2
D = 0.014 + 0.07CL
k1 = 0.02
Kuc = 4.5?10?5
b = 20m
T = 65000N
h = 2.5m
S = 90m2
r = 0.035
CLmax = 1.5
N = 3
e = 0.9
hOB = 12m
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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This post was last modified on 04 November 2019