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Design and Analysis of Subsonic Thrust Vectoring Nozzle using CFD and
Optimization of Nozzle parameters
Conference Paper · April 2016
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National Cheng Kung University
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Design and Analysis of Subsonic Thrust Vectoring Nozzle using CFD
and Optimization of Nozzle parameters
D.Daljit Majil1, B.tech-Aeronautical, Vel Tech Dr.RR&Dr.SR Technical University, Chennai
Mobile No: 9585154285 mail id:daljit.ae13@veltechuniv.edu.in
S.Guruprasaath2, B.tech-Aeronautical, Vel Tech Dr.RR & Dr.SR Technical University, Chennai
Mobile No: 9025252606 mail id:gurulovesspace@gmail.com
Abstract
This paper is dealing with the design
of Thrust vectoring Nozzle using CFD
analysis for 2D nozzle design on which flow
takes place at Subsonic speed and it is
analyzed to the variation in various
deflection angle and Flow Parameters. Flow
Parameters such as Pressure, velocity and
mass flow rate are noted and Thrust
generation will be calculated with the help
of this Flow parameters. Same procedure is
repeated for different deflection angle of
nozzle. Main objective of this paper is to
optimize the effectiveness of Deflection
angle in the TVC Nozzle. Hence calculated
numerical values are used to plot the graph
between Deflection angle vs Thrust. Another
Graph which graphically represents the
proportionality between the difference in
Thrust and Deflection angle of Nozzle.
Hence effectiveness of Deflection angle is
optimized to increase the application of
Thrust Vectoring in Subsonic Aircrafts.
Vi
Inlet Velocity
ms-1
Ve
Exit Velocity
ms-1
Pi
Inlet Pressure
Kgm-2
Pe
Outlet Pressure
Kgm-2
mi
Inlet Mass flow rate Kg/s
me
Outlet Mass flow rate Kg/s
LD
Length of the Duct
cm
Di
Inlet Diameter
cm
De
Diameter of Outlet
cm
TF
Thrust Force
N
LN
Length of the Nozzle cm
Nomenclatures
Abbreviations
CFD
Computational Fluid Dynamics
TVC
Thrust Vector Control
TV
Thrust Vector
Ɵ
Deflection Angle
Deg
UAV Unmanned Aerial vehicle
Ai
Inlet Area
m2
UCAV Unmanned Combat Aerial Vehicle
Ae
Exit Area
m2
VTOL Vertical Takeoff and Landing
STOL Short range Takeoff and Landing
1. Introduction
Thrust vectoring is one of the major
phenomena used in Supersonic Fighter
Aircrafts
for
VTOL/STOL
and
Maneuvering. In an Aircraft TVC is
obtained by changing the direction of
Exhaust gas to certain angle by which
direction of thrust is being changed.
Normally TVC can be achieved by two
types namely,
1. Mechanical Thrust vectoring
2. Fluidic Thrust vectoring
Mechanical Thrust Vectoring
In mechanical thrust vectoring, it
involves deflecting the engine nozzle thus
physically changing the direction of primary
jet which changes the direction of thrust.
Fluidic Thrust Vectoring
Fluidic thrust vectoring system
involves injection of fluid to the primary jet
which changes the direction of primary jet to
certain angle. Hence TVC is obtained.
Geometrical Parameters of TVC nozzle 2D model
A TVC nozzle that is going to analyze will
have some standard constant geometric
parameters. They are illustrated following
table,
Inlet diameter(Di)
80cm
Outlet diameter(De)
50cm
Length of the Duct(LD)
60cm
Length of the Nozzle(LN)
40cm
2. Thrust Vectoring Nozzle
Experimental study is one of the
methods to engineering problems, but this
method is very costly. Hence this difficulty
can be rectified by CFD.In the CFD problem
is simulated to software and it proves for
efficient tool and also analysis for various
flow parameters.
A TVC nozzle consists of two kinds of
parameters. They are,


Geometrical Parameters
Flow Parameters
Flow Parameters of TVC nozzle 2D model
Similarly, a TVC nozzle is analyzed with
some constant flow parameters throughout
the simulation they are illustrated in
following table,
Inlet velocity(Vi)
100m/s
Exit Pressure(Pe)
1033.127 Kg/m2
Inlet mass flow rate(mi)
61.495 Kg/s
In the above table, Flow parameters such as
Inlet Velocity, Exit Pressure and mass flow
rate at inlet section is maintained constant.
In boundary condition setup inlet is selected
as velocity inlet with the value of 100m/s
and exit pressure of 1033.127 Kg/m2 which
is nothing but the value of standard
atmospheric pressure. And with the help of
following equation, mass flow rate has been
calculated.
m=ρAV
In above equation ρ is density of fluid flow
(1.225 Kg/m3).A represents the Inlet Area
i.e. Cross sectional area of Inlet section and
V gives the value of Velocity at Inlet.
Constant
Boundary
Condition
Inlet-Velocity
inlet=100m/s
Outlet-Pressure
outlet=1033.127 Kg/m2
Solution
Solution initializationStandard-Compute from
Inlet
Run calculation-200
iterations
Results
Velocity contours and
Pressure contours
Simulation carried out with these boundary
conditions for various cases, various cases
are illustrated in table below,
Case
Deflection Angle(Ɵ)
1
0
2
10
3
20
4
30
5
40
3. CFD Simulation
For CFD Analysis of TVC nozzle, Ansys
14.5 software is used for flow simulation.
Nozzle is being designed in ansys fluent.
Analysis procedure is carried out with
following setup
Procedure
Details
Solution SetupGeneral
Type-Pressure based
Velocity FormulationAbsolute
Time-Steady
2D space-Planar
Energy Equation-Off
Viscous-K-epsilon
Fluid-Air, Density-
Models
Materials
Deflection angle of Nozzle is measured with
respect to Center axis of the nozzle, Hence
simulation has been done for various
deflection angle shown in table above.
4. Simulation Procedure
a) Nozzle has been drawn along with
the duct of length LD 60cm and with
required dimensions.
b) The surface from the edges of sketch
has been generated.
c) Meshed it with Fine meshing and On
the proximity and the curvature in
the sizing of meshing.
d) Named the edges that Inlet, Wall and
Outlet of the nozzle.
e) Analysis procedure has been carried
out
with
required
boundary
conditions mentioned above.
f) Initialized the solution with standardCompute from Inlet condition.
g) Solution is calculated for 200
iterations(upto solution is converged)
h) Velocity contour and Pressure
Contour has been made that
illustrates the variation Pressure and
Velocity in the TVC nozzle. Probe
value has been taken at Inlet and
Outlet.
i) Same procedure has been repeated
for different cases i.e. different
deflection angle of Nozzle. And
values of Flow parameters has been
noted and tabulated.
With the reference of general thrust
equation, Thrust force has been
calculated with the help of various flow
parameters measured. General Thrust
equation is
TF=me.ve-mi.vi+ (δP.Ae)
=me.ve-mi.vi+ (Pe-Pi).Ae
Simulation is carried out by following
parameters mentioned in table for different
cases; simulation has been carried for only
different with same flow parameters,
Case
Inlet Velocity(Vi)
Outlet Pressure (Pe)
1(0deg)
100m/s
1033.127 Kg/m2
2(10deg)
100m/s
1033.127 Kg/m2
3(20deg)
100m/s
1033.127 Kg/m2
4(30deg)
100m/s
1033.127 Kg/m2
5(40deg)
100m/s
1033.127 Kg/m2
5. Result
5.1Velocity contour (Ɵ=0deg)
5.2Pressure Contour (Ɵ=0deg)
5.3Velocity Contour (Ɵ=10deg)
5.4Pressure Contour (Ɵ=10deg)
5.5Velocity Contour (Ɵ=20deg)
5.6Pressure Contour (Ɵ=20deg)
5.7Velocity Contour (Ɵ=30deg)
5.8Pressure contour (Ɵ=30deg)
5.9Velocity Contour (Ɵ=40deg)
5.10Pressure Contour (Ɵ=40deg)
By the general thrust equation, Exit Velocity
Ve is one of the main parameter on which
both Thrust force and mass flow rate are
depending.
Deflection Angle(Ɵ)
In Deg
Exit Velocity(Ve)
m/s
0
163.59
10
163.92
20
164.806
30
165.401
40
166.173
Difference in pressure between Inlet Pi and
Outlet Pe that determines the Exit Velocity
Ve. Thus values are tabulated,
6. Discussion on Contour result
By the reference of simulation and contour
result, Velocity at exit area Ve is increased
with deflection angle. This takes place due
to increase of pressure at the top surface of
the Nozzle wall. Pressure increase in nozzle
wall is due to flow separation and vortex
flow formation. Various flow parameters has
been measured in the simulation process,
hence they are tabulated below with respect
to various deflecting angle,
Deflection Angle(Ɵ)
In Deg
Inlet pressure(Pe)
Kg/m2
0
11353.92
10
11359.43
20
11360.45
30
11366.47
40
11372.283
By the formula of Mass flow rate, Velocity
is proportional to Mass flow rate which is
one of the main parameter on which Thrust
force is depending,
Deflection
Angle(Ɵ)
In Deg
Mass Flow rate at
Exit(me)
Kg/s
20
949.96
30
1435.83
0
39.27
40
2041.17
10
39.35
20
39.56
30
39.71
40
39.89
7. Graphical representation
With the values such as Exit Velocity Ve,
Inlet Pressure Pi and Mass flow rate at
Outlet me for different cases i.e. different
deflection angle TVC nozzle Thrust Force
has been calculated with the help of General
Thrust Equation. Thrust Value has been
tabulated below,
Deflection Angle(Ɵ)
In Deg
Thrust
TF
N
0
4653.4
10
4919.8
20
5603.36
30
6089.23
40
6694.57
7.1 Ɵ vs Ve
Since we got difference in flow parameters
with respect to Deflection Angle of TVC
nozzle. So there will be difference in Thrust
force that can be tabulated as,
Deflection Angle(Ɵ)
In Deg
Diff. in Thrust
δTF
N
0
0
10
266.4
7.2 Ɵ vs Pi
7.3 Ɵ vs me
7.5 Ɵ vs δTF
8. Conclusion
By the analysis of subsonic TVC nozzle for
2D model, Effectiveness of Deflection
Angle Ɵ has been optimized. Which gives
the result of increase in Thrust force TF,
Hence by this analysis and optimization of
Nozzle parameters such as Exit velocity Ve,
Inlet pressure Pi and Mass flow rate at
Outlet me is directly proportional to one of
the Geometric parameter of TVC Nozzle i.e.
Deflection angle Ɵ.
7.4 Ɵ vs TF
The Above Graphs represent Increase in
Various flow parameters on which Thrust is
depend. Following Graph represents the
Difference in Thrust Force TF between
deflection angles.
With the result of this analysis and
optimization TVC nozzle suitable for
various UAV, UCAV and Unconventional
tailless Aircrafts which will be operated at
subsonic Speed. With the help of TVC
nozzle UAVs can
perform quick
maneuverability at various hazardous zone
while aerial photography where the
conventional Aerodynamic Control surfaces
may not be sufficient to make quick
maneuverability .TVC can perform a
Pitching and yawing movement and Also
VTOL/STOL.
9. References
1. Mark S. Mason, William J. Crowther;
Fluidic Thrust Vectoring on Low
Observable Aircraft, CEAS Aerospace
Aerodynamic Research Conference, 10-12
June 2002, Cambridge, UK
2. P.Parthiban, M.Robert Sagayadoss,
T.Ambikapathi; Design and analysis of
rocket engine nozzle by using cfd and
optimization of nozzle parameters,
International Journal on Engineering
Research-online,Vol.3., Issue.5., 2015(Sept.
–Oct.).
3.Jose Pascoa, Antonio Dumas, Michele
Trancossi, Dean Vucinic; A review of
thrust-vectoring in support of a V/STOL
non-moving
mechanical
propulsion
system, Central European Journal of
Physics., July 2013
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