Aircraft Design Lab
Design Problem: 6
Rudder Design Problem
A large transport aircraft with a maximum take-off mass of 2, 60,000 kg is equipped with four
turbofan engines each generating 140 KN of thrust. The distance between the most aft and the most
for

Aircraft Design Lab
Design Problem: 5
Elevator Design Problem
Design an elevator for the aircraft which has the following characteristics.
Take-off mass ( m )
V
= 20,000 kg, Stall Velocity ( stall )
I
= 43.73 m/s, Moment of Inertia about y-axis ( yy )
V
=

Aircraft Design Lab
Design Problem: 7
Aileron Design Problem
The aircraft has a conventional configuration and the following geometry and weight characteristics:
2
2
2
m=6,500 kg ; S=21 m ; AR=10 ; =0.7 ; Sh=5.3 m ; S V =4.2 m ; V S =80 knot ;
CL =
W
4.51

Sensitivity of Take-off weight versus Range:
The sensitivity of take-off weight versus range is found by considering the cruise range. It involves
using Breguet Partials and the equation is described as below:
WTO
L 1
F * C j * V *
R
D
Equation 10: Equat

Calculate the pressure, density and temperature at 7, 15 and 24 km using ISA
Model of Atmosphere.
Input: Height (Altitude)
Output: Atmospheric Properties (Temperature, Pressure and Density)
h1=11; h2=20; h3=32;
% Altitudes in kilometer
a0=-6.5e-3; a2=1e-3

Aircraft Design Lab
Design Problem 1:
International Standard Atmosphere Model (ISA)
Create a function file (atmSI.m) to estimate pressure, temperature, density, and speed
of sound in SI units at different altitude ranges from 0 km to 32 km.
Input: Height

Particle Dynamics
Derivative of a Vector:
Consider a vector A ( t ) which is a function of time. The derivative of
A
with respect to time is defined as,
(t )
A ( t+ t ) A
lim
dA
A
t0
= lim
=
dt t 0 t
t
A vector has magnitude and direction, and it change

Aircraft Design Lab
Design Problem: 1
Preliminary Weight Estimation
A 480 seater Jet airplane cruising at M=0.84, at 11 km altitude (speed of sound = 296.6 m/s)
and having a range of 9800 km is considered. The number of flight attendants is regulated by
F

Aircraft Design Lab
Design Problem: 2B
Constraint Analysis
=
The installed full throttle thrust lapse, which depends on altitude, speed, and whether or not an afterburner
is operating.
=how much fuel has been consumed payload delivered
T SL=
Refer to the

Aircraft Design Lab
Design Problem: 2
Constraint Analysis
Performance requirements imply a functional relationship between Power to Weight ratio (P/W) and
Wing Loading (W/S).
For each phase of flight, the power to weight ratio is calculated in terms of wi

The satellite is rotating about the z axis at a constant rate N. The xyz axes
are attached to the spacecraft, and the z-axis has a fixed orientation in
inertial space. The solar panels rotate at a constant rate in the direction
shown. Relative to point O,

Aircraft Design Lab
Design Problem: 6
Rudder Design Problem
A large transport aircraft with a maximum take-off mass of 2, 60,000 kg is equipped with four
turbofan engines each generating 140 KN of thrust. The distance between the most aft and the most
for

Aircraft Design Lab
Design Problem: 7
Aileron Design Problem
The aircraft has a conventional configuration and the following geometry and weight characteristics:
In the design process of an aileron, four parameters need to be determined. They are: 1. aile

Aircraft Design Lab
Design Problem: 5
Elevator Design Problem
Design an elevator for the aircraft which has the following characteristics.
Take-off mass (mTO ) = 20,000 kg, Stall Velocity (Vstall ) = Rotational Velocity (VR ) =
43.73 m/s, Moment of Inerti

Aircraft Design Lab
Design Problem: 1
Preliminary Weight Estimation
A 700 seater jet airplane cruising at M=0.8, at 11 km altitude (speed of sound =
296.6 m/s) and having a range of 9500 km is considered. The number of flight
attendants is regulated by FA

Aircraft Design Lab
Design Problem: 2B
Constraint Analysis
The installed full throttle thrust lapse, which depends on altitude, speed, and whether or not an afterburner is
operating.
Refer to the "installed" engine thrust, which is generally less than the

Aircraft Design Lab
Design Problem: 2
Constraint Analysis
Performance requirements imply a functional relationship between Power to Weight ratio (P/W) and
Wing Loading (W/S).
For each phase of flight, the power to weight ratio is calculated in terms of wi

Aircraft Design Lab
Design Problem: 2A
Constraint Analysis
Consider a 700 seater jet aircraft whose maximum take-off weight is to be
determined to be 20000 lbs and the aircraft CD0 is determined to be 0.025. By using
the matching plot technique, determine

Aircraft Propulsion-I
Presentation Contents
Performance of Jet Engines
Notation and Station Numbering
Intake
Compressor
Combustion Chamber
Turbine
Nozzle
Ideal Turbojet Cycle
Performance of Jet Engines
In Previous slides we represented a gas turbine engin