UWE Bristol Engineering showcase 2015

Samuel Hill
Meng Part A Aerospace Design Engineering
Project Supervisor
Dr. Oluwamayokun B. Adetoro
Ph.D. Meng MRAeS
Design and Numerical Analysis of a Scramjet Inlet
This project is an investigation into Scramjet design and analysis with potential to expand the design to accommodate ramjet/scramjet
transition at Mach 6. The literary review consisted of investigation into the application of scramjets, potential problems encountered
while travelling at hypersonic speeds and possible design solutions. In order to validate the use of computational fluid dynamics wind
tunnel testing ensued. The tunnel was modelled using the computational software ANSYS Fluent and comparison was made to real
practical test results. Once this was completed the inlet was designed based on the ‘shock on lip’ criterion and oblique shock charts and
equations were used to find the optimum geometry. This geometry was then analysed using ANSYS Fluent and the performance was
evaluated.
Computational Validation
The supersonic wind tunnel in the universities fluid dynamics laboratory was
analysed numerically in order to validate the use of computational software.
The picture to the left represents the distribution of static temperature along
the wind tunnel constructed through computational analysis. The results of
which are very comparable to that of practical tests.
Initial Design
Hypersonic vehicle inlets harness the kinetic energy of the incoming air to
generate shock waves the compress to oncoming air to a desired value
perfect for combustion to take place. The design constructed for analysis was
created by the use of the oblique shock relations. The equations which
describe such will predict the aerodynamic characteristics succeeding a shock
wave. These equations are used to predict the geometry which would create
optimum conditions leaving the inlet.. This geometry is constructed through
the use of CAD software SolidWorks and is shown to the left. The Inlet will be
situated on the abdomen of the vehicle body to allow integration into a
waverider vehicle design.
Project summary
This study will focus on the modelling and the design
of the inlet section or isolator section whilst
considering different flow conditions and operating
conditions. This will predominantly be conducted
using computational fluid dynamic (CFD) simulations,
whist demonstrating the use of appropriate CFD
solver, accurate modelling and appropriate
assumption made; hence the results must be well
validated.
Project Objectives
The desired output of this project will be validation of
use of numerical techniques as well as an inlet design
from which future research can benefit from. If a
company would wish to construct a hypersonic
vehicle with this mission profile this project may be
useful.
Project Conclusion
This project has validated the authors use of
Computational Fluid Dynamic Software. Secondly the
use of oblique shock equations and charts are
adequate for the construction of simple hypersonic
inlet designs. The software ANSYS Fluent is capable of
modelling the complex aerodynamics of hypersonic
air intake as proven in the comparison section of this
study, in which numerically generated results are
compared to those calculated theoretical y.
Computational Analysis
Computational analysis is conducted on the specified geometry to analyse
the performance of the designed inlet. The resulting performance is as
shown:
Theoretical CFD Run 1 CFD Run2
Total Pressure Ratio 0.941187877 0.941942284 0.949762764
Adiabatic Compression
Efficiency
0.672166124 0.708740605 0.741988651
Kinetic Energy Efficiency 0.983289033 0.983306693 0.987638376