MAE 457: Flight Vehicle Stability and Control
Homework Assignment 4
Due: Thursday, Feb. 12, at the beginning of class
Instructions:
1. Start each problem on a new sheet. You need to complete all probl
MAE 457: Flight Vehicle Stability and Control
Homework Assignment 5
Due: Thursday, March 5, at the beginning of class
Instructions:
1. Start each problem on a new sheet. You need to complete all probl
MAE 457: Flight Vehicle Stability and Control
Homework Assignment 7
Due: Tuesday, March 31, at the beginning of class
Instructions:
1. Start each problem on a new sheet. You need to complete all probl
MAE 457: Flight Vehicle Stability and Control
Homework Assignment 6
Due: Thursday, March 19, at the beginning of class
Instructions:
1. Start each problem on a new sheet. You need to complete all prob
MAE 457: Flight Vehicle Stability and Control
Homework Assignment 1
Due: Thursday, Jan. 22, at the beginning of class
Instructions:
1. Start each problem on a new sheet. You need to complete all probl
NORTH CAROLINA STATE UNIVERSITY
DEPARTMENT OF MECHANICAL AND AEROSPACE ENGINEERING
MAE 457 Flight Vehicle Stability and Control
Course Syllabus Spring 2015
INSTRUCTOR
Dr. Matthew Bryant
Office: 3407 E
MAE 457: Flight Vehicle Stability and Control
Homework Assignment 2
Due: Thursday, Jan. 29, at the beginning of class
Instructions:
1. Start each problem on a new sheet. You need to complete all probl
Problem 1, part a, c, d, b, and e
From page 2.27 in notes, or
book eqs. (2.2,4)+(2.2,9)+Cmp
+
Problem 2
2.17 ft
19.80 ft
b)
-[^yrz",>l"l
'YJ,
-so
=
i
1s
rZ
L
41 =
I
=
5
zr r,)
= zsJ7.rcfw_t
rrz
ct
\4-
2
Note: In this solution, S1 is taken as the area of the first
panel for both the LH and RH sides of the wing.
Likewise for S2.
This is different from the lecture notes, where I used S1
as the area of
HW 2, Prob 1
Cmac = 0.045
Note: Cmcg (at CL = 0) for
flying wing is same as Cmac, as
seen from the Equation:
Cmcg = Cmac + CL(h - hnw)
Aft
Fwd cg
0.45
0.9
FRL
Trim condition
Zero- condition
Zero-CL co
Solutions for Homework 1
Problem 3 (20 points)
(i) Multiple Choice: The symbols p, q, and r in aircraft flight dynamics denote:
a. yaw, pitch, and roll rates about the aircrafts body axes
b. yaw, pitc
l,/cLn
fK La v o.f of
*
fn-r,
S'/"b,'/,f/
t<-
L f,ntt #,*,
Decfw_,h"|'io't ocfw_
-cfw_kytil".l
f
/c.
l'/
5"
fon,
( Sr.
S*1,'/7, (,a,tw I , E?o,'l'l.,Ln
/.
i)
of Rr#nno, ( sr. f ,>" / cfw_)
- Efo,/1.,t
MAE 457: Flight Vehicle Stability and Control
Project 1 (Analysis Project): Part A
Due: Thursday, March 26
Objective
The overall aim of this project is to estimate the stability and control characteri