Flight Dynamics 1
1. Derive the Z force equation from the basic equation of motion in chapter 2 to the transformed
equation in chapter 6. Show all your work and follow the steps below:
i) Starting with the Z force equation 2.55, linearize it to obtain eqn
Chapter 4
5) Show that (*/w) dp/dx is proportional to the ratio of pressure
force to wall friction force on the fluid in a boundary layer. Show that
it is constant for any of the Falkner Skan wedge flows.
21)
: dp / dx 0
u
2u
Ue
2
x
y
If
ue 2( x 1 ) ;
3-1.for incompressible constant-property, planner unsteady
flow, write the energy equation using a stream
function.
u2
) c dT d ( u 2 / 2 )
2
u2
u( e
)dy
2
( u )
u2
u2
u
dx ( e
(e
)dx dy
x
2 x
2
de d (
u2
( e
)dx
2
( )
u2
u2
dy ( e
(e
)dy d
Chapter 1
1. Calculate the Re No. based on length for a 1 m flat plate in an
airstream at sea-level at 25 C with a velocity of 3 m/s. Then calculate
the Re No. based on diameter for a water at 25C flowing at 150
cm3/s through a tube of diameter 1 cm.
25+2
In the Name of GOD
Flight Mechanics, 89-90 (II)
HW. # IV, Due 3-24-90
1. We will consider two types of aircraft:
A) A single, propeller driven a/c, approximately having the following characteristics,
designated as CP-1
bwing = 35.8 ft, S = 174 ft2, Wempty