mdts 5734 : aerodynamics & propulsiondynlab.mpe.nus.edu.sg/mpelsb/mdts/aero n1 v3.pdf · g....
TRANSCRIPT
G. Leng, MDTS, NUS
MDTS 5734 : Aerodynamics & Propulsion Lecture 1 : Characteristics of high speed flight
G. Leng, MDTS, NUS
References
• Jack N. Nielsen, “Missile Aerodynamics”, AIAA Progress in Astronautics and Aeronautics, v104, 1986
• Michael J. Hemsch (ed), “Tactical Missile Aerodynamics : General Topics”, AIAA Progress in Astronautics and Aeronautics, v141, 1992
• Michael R. Mendenhall (ed), “Tactical Missile Aerodynamics : Predicition Methodology”, AIAA Progress in Astronautics and Aeronautics, v142, 1992
• Gordon E. Jensen, David W. Netzer, “Tactical Missile Propulsion”, AIAA Progress in Astronuatics and Aeronautics, v 170, 1996
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Training Programme
1. Characteristics of supersonic flight
or the aerodynamic forces on the missile
2. Missile propulsion for high speeds
or rockets, ramjets and scamjets
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Question : Is the Earth’s atmosphere uniform ?
0 km 20 km
Air pressure (N/m2) 101 325 6000
Air density (kg/m3) 1.225 0.1
Air temperature (oC ) 30 -60
Question :Any implications for missiles ?
1.1 The Earth’s Atmosphere
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1.2 Aerodynamic forces
Aerodynamic forces on a flight vehicle scale as :
Aerodynamic force V2
Air speed
Air density
Note the dependence on V2
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For missiles, there are two important aerodynamic forces
Axial force A = ½ V2 S CA
Normal force N = ½ V2 S CN
N
A
These forces are aligned with the missile body and not the velocity
V
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The symbols are :
S : reference area (m2) e.g. missile cross section area
CA : axial force coefficient (non dimensional)
CN : normal force coefficient (non dimensional)
½ V2 : dynamic pressure ( N/m2)
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L
D
V
Equivalently we can represent the aerodynamics forces as
lift and drag forces aligned with the velocity
Lift force L = ½ V2 S CL
Drag force D = ½ V2 S CD
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Example : Estimate CL for the AGM 65
Flight conditions
mass : 300 kg speed : 320 m/s
altitude : S.L diameter : 0.3048 m
For level flight,
CL =
=
=
S.L.
S =
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1.3 Aerodynamic flow parameters
Missile airspeeds can range from 100 – 103 m/s
Aerodynamic properties are determined by the Mach number M
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Question : Why does the speed of sound come in ?
1. Air is compressible.
2. A moving missile disturbs the surrounding air
3.These disturbances e.g. pressure variations, take a finite time
to propagate at the speed of sound through the surrounding air
4. The Mach number measures the importance of this
compressibility effect .
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1.3.1 Classification of flow regimes via Mach number
• M < 0.8 subsonic incompressible aerodynamics
• 0.8 < M < 1.2 transonic localized compressibility effects
• 1.2 < M < 5 supersonic compressible aerodynamics
• M > 5 hypersonic aerodynamic heating
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Example : Disturbance propagation M < 1
distrubance
missile
Consider the distances travelled by the disturbance and the missile in 1s
a
V 0
What about the
disturbance created
mid way ?
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Example : Disturbance propagation M > 1
distrubance
missile
Consider the distances travelled by the disturbance and the missile in 1s
a
V 0
sin = a/V
= 1/M
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So for M > 1, there is a discontinuity in the flow field “seen”
by the missile
Air properties like pressure, temperature and density changes
sharply across the discontinuity or shock
Schlieren photo of shock
waves
Question : Can you
estimate the Mach number ?
Light is refracted
differently because of
changes in air density
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The shape of the shock wave depends on the shape of the object
blunt nosed
object
detached
shock
Shocks created by high speed flight can be annoying ....
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1.4 The placement of lift surfaces
Question : Can this missile fly at Mach 3 ?
= 25o
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The angle of the attached shock is related to the Mach number by :
sin = 1/M
At Mach 3, = sin-1 (1/3)
= 19.5o
= 19.5o
Is this a good design ? What is the max speed of this missile ?
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2.1. The design of supersonic airfoils
For efficient lift generation at subsonic speeds, airfoils look like :
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So why can’t a similar airfoil work at transonic/supersonic speeds ?
subsonic region shock
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2.2 Drag variation with speed
1. As a missile approaches M = 1, drag increases significantly
2. This is known as the transonic drag rise
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3. Missiles have to pass through this transonic drag rise to get
to supersonic speeds
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1. Critical aerodynamic surfaces are swept back to reduce this
transonic drag rise
2.3 Drag reduction using sweepback
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2. This works because ...
wing
M
velocity vector
Mn
normal component
... the wing “sees” a
lower effective airspeed
Mn = M cos
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An “interesting” example of the use of sweepback
Me 262 – first operational jet fighter
What is the moral of the story ?
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Example : So what can you deduce from the
sweep back angle ?
Maverick AGM = 80 o
Bloodhound SAM = 26 o
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2.4 Drag reduction using the Area-Rule
Near Mach 1,
the drag of a slender wing-body combination
is equal to
that of a body of revolution having the same
cross-sectional area distribution
What does this mean ?
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A : slender body
B : Wing-body combination
with higher drag
C : Equivalent body of
revolution for wing-body B
D : “Pinched” body
A, i.e. lower drag c/o B