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Dissertations / Theses on the topic 'Supersonic inlets'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 July 2025

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1

Titchener, Neil. "An experimental investigation of flow control for supersonic inlets." Thesis, University of Cambridge, 2013. https://www.repository.cam.ac.uk/handle/1810/245531.

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This thesis focuses on the control of shock wave / boundary layer interactions (SWBLIs) in supersonic inlets. The overall aim of this study is to determine to what extent vortex generators (VGs) can mitigate flow separations within supersonic inlets. To achieve this, an experimental investigation was undertaken in a small-scale wind tunnel, because small-scale wind tunnels are much more amenable to numerous measurement techniques than real inlets. A new geometry was designed and developed as part of this study to make the configuration more representative of typical inlet conditions than previ

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2

Pande, Abhijit. "Effect of struts on aeroacoustics of axisymmetric supersonic inlets." Thesis, This resource online, 1994. http://scholar.lib.vt.edu/theses/available/etd-07292009-090449/.

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3

Miller, Kevin C. "Comparison of the aeroacoustics of two small-scale supersonic inlets." Thesis, This resource online, 1996. http://scholar.lib.vt.edu/theses/available/etd-11012008-063024/.

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4

Warren, Arthur H. "Propulsion system analysis for conceptual design : drag and losses of nozzles and mixed compression inlets /." Thesis, This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-07112009-040259/.

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5

Malo-Molina, Faure Joel. "Numerical study of innovative scramjet inlets coupled to combustors using hydrocarbon-air mixture." Diss., Georgia Institute of Technology, 2010. http://hdl.handle.net/1853/33906.

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To advance the design of hypersonic vehicles, high-fidelity multi-physics CFD is used to characterize 3-D scramjet flow-fields in two novel streamline traced configurations. The two inlets, Jaws and Scoop, are analyzed and compared to a traditional rectangular inlet used as a baseline for on/off-design conditions. The flight trajectory conditions selected are Mach 6 and a dynamic pressure of 1,500 psf (71.82 kPa). Analysis of these hypersonic inlets is performed to investigate distortion effects downstream with multiple single cavity combustors acting as flame holders, and several fuel injecti

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6

Webb, Nathan Joseph. "Control of Supersonic Mixed-Compression Inlets Using Localized Arc Filament Plasma Actuators." The Ohio State University, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=osu1274714729.

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7

Thammavichai, Jackkrit. "Effects of compressor face boundary conditions on the dynamic behavior of supersonic inlets." Thesis, Massachusetts Institute of Technology, 1996. http://hdl.handle.net/1721.1/47397.

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8

Detwiler, Kevin P. "Reduced fan noise radiation from a supersonic inlet." Thesis, This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-09192009-040457/.

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9

Nuckolls, William E. "Fan noise reduction from a supersonic inlet." Thesis, This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-08222009-040447/.

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10

Wagner, Robert. "Aeroacoustics of the bifurcated 2D supersonic inlet." Thesis, Virginia Tech, 1995. http://hdl.handle.net/10919/45084.

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An investigation was performed to determine the aerodynamic and acoustic performance of the bifurcated 2D supersonic inlet during takeoff and approach flight conditions, and to compare these results indirectly to those of the axisymmetric supersonic inlet. The comparison is not direct since the centerbody position of the bifurcated 2D inlet is set at takeoff and approach position, where as the axisymmetric inlet’s centerbody position is not. The axisymmetric inlet’s aeroacoustic performance data is to serve as a reference to evaluate the bifurcated 2D inlet’s aeroacoustic performance. The inle

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11

Hongprapas, Sorarat. "Preliminary experiment and analysis of supersonic inlet buzz." Thesis, This resource online, 1996. http://scholar.lib.vt.edu/theses/available/etd-01312009-063329/.

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12

Najafiyazdi, Alireza. "Theoretical and numerical analysis of supersonic inlet starting by mass spillage." Thesis, McGill University, 2007. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=111524.

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Supersonic inlet starting by mass spillage is studied theoretically and numerically in the present thesis. A quasi-one-dimensional, quasi-steady theory is developed for the analysis of flow inside a perforated inlet. The theory results in closed-form relations applicable to flow starting by the mass spillage technique in supersonic and hypersonic inlets.<br>The theory involves three parameters to incorporate the multi-dimensional nature of mass spillage through a wall perforation. Mass spillage through an individual slot is studied to determine these parameters; analytical expressions for thes

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13

Alemdaroglu, Mine. "Conceptual Internal Design And Computational Fluid Dynamics Analysis Of A Supersonic Inlet." Master's thesis, METU, 2005. http://etd.lib.metu.edu.tr/upload/2/12606026/index.pdf.

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ABSTRACT CONCEPTUAL INTERNAL DESIGN AND COMPUTATIONAL FLUID DYNAMICS ANALYSIS OF A SUPERSONIC INLET ALEMDAROgLU, Mine M. S., Department of Aerospace Engineering Supervisor: Prof. Dr. Yusuf &Ouml<br>ZY&Ouml<br>R&Uuml<br>K May 2005, 144 pages In this thesis, the conceptual internal design of the air inlet of a supersonic, high altitude, solid propellant ramjet cruise missile is performed. Inviscid, compressible CFD analysis of the designed inlet is made in order to obtain qualitative and quantitative performance characteristics of the inlet at different operating conditions. The conceptu

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14

Esterhuyse, J. C. "Aerodynamic drag of a two-dimensional external compression inlet at supersonic speed /." [S.l. : s.n.], 1997. http://dk.cput.ac.za/cgi/viewcontent.cgi?article=1033&context=td_ctech.

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15

Bellinger, James. "Control of the oblique shockwave/boundary layer interaction in a supersonic inlet." Connect to resource, 2008. http://hdl.handle.net/1811/32065.

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16

Baig, Saood Saeed. "A simple moving boundary technique and its application to supersonic inlet starting /." Thesis, McGill University, 2008. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=112555.

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In this thesis, a simple moving boundary technique has been suggested, implemented and verified. The technique may be considered as a generalization of the well-known "ghost" cell approach for boundary condition implementation. According to the proposed idea, the moving body does not appear on the computational grid and is allowed to move over the grid. The impermeable wall boundary condition is enforced by assigning proper gasdynamic values at the grid nodes located inside the moving body close to its boundaries (ghost nodes). The reflection principle taking into account the velocity of the b

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17

Esterhuyse, JC. "Aerodynamic drag of a two-dimensional external compression inlet at supersonic speed." Thesis, Cape Technikon, 1997. http://hdl.handle.net/20.500.11838/1297.

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Thesis (DTech (Mechanical engineering))--Cape Technikon, 1997<br>This study forms the basis from which the aerodynamic drag of a practical supersonic inlet can be predicted. In air-breathing propulsion systems, as used in high performance flight vehicles, the fuel is carried onboard and the oxygen required for combustion is ingested from the ambient atmosphere. The main function of the inlet is to compress the air from supersonic to subsonic conditions with as little flow distortion as possible. When the velocity of the vehicle approaches or exceeds sonic velocity (M = 1,0) a number of con

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18

Saunders, Christopher A. II. "Noise Reduction in an Axisymmetric Supersonic Aircraft Inlet using Trailing Edge Blowing." Thesis, Virginia Tech, 1998. http://hdl.handle.net/10919/31385.

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Acoustic experiments were conducted in an anechoic chamber with a 1/14th scale model of a supersonic aircraft engine inlet using Trailing Edge Blowing (TEB) to reduce the engine fan noise from a turbofan propulsion simulator (TPS). The TPS is 4.1 in. (10.4 cm) in diameter and is powered by compressed air. The supersonic inlet is connected to the TPS and is geometrically and acoustically scaled from a working design. The supersonic inlet is operated in a takeoff or landing operating condition where the inlet core flow is subsonic. TEB is the process of ejecting high pressure air to re-energ

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19

Ahsun, Umair 1972. "Dynamic characterization and active control of unstarts in a near-isentropic supersonic inlet." Thesis, Massachusetts Institute of Technology, 2004. http://hdl.handle.net/1721.1/17752.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2004.<br>Includes bibliographical references (p. 97-98).<br>A near-isentropic supersonic inlet, at Mach 2.2, has been designed to give enhanced recovery and thus increased range for a supersonic transport aircraft. In such a design a mixed compression inlet design is typically used. Enhanced recovery of 97% in total pressure is achieved by reducing the unstart-tolerance of the inlet and by an efficient boundary layer control mechanism. Thus the resulting inlet design has reduced stability to unstart in

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20

Kozak, Jeffrey D. "3-D flow calculations of a bifurcated 2D supersonic engine inlet at takeoff." Thesis, This resource online, 1995. http://scholar.lib.vt.edu/theses/available/etd-03032009-040729/.

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21

Svensson, Marlene. "A CFD Investigation of a Generic Bump and its Application to a Diverterless Supersonic Inlet." Thesis, Linköping University, Department of Management and Engineering, 2008. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-12490.

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<p>This is a Master Thesis done at the Swedish Defence Research Agency with the purpose to design and investigate how different geometries of a compression surface integrated with an intake affects the performance such as distortion, boundary layer diversion, pressure recovery and deceleration of speed.</p><p>The work was divided in two parts. In the first part, CFD calculations using the FOI developed Edge 4.1 code were made for the compression surfaces alone. In the second part the most promising design was integrated with an intake. Two more bumps with the intake were modelled and the three

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22

Nieberding, Zachary J. "An Investigation of Acoustic Wave Propagation in Mach 2 Flow." University of Cincinnati / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1406881591.

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23

Wang, Peng C. "Large eddy simulation of high speed convergent-divergent nozzle flows." Thesis, Loughborough University, 2013. https://dspace.lboro.ac.uk/2134/11937.

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Interest in developing a detailed understanding of jet plume aerodynamics has increased significantly in recent years, for both civil (noise reduction) and military (Infra-Red signature modelling) aerospace applications. Such flows are critically dependent on turbulence modelling of the jet plume shear layer mixing. Reynolds averaged Navier Stokes (RANS) CFD tends to overpredict while Large Eddy Simulation (LES) CFD underpredicts potential core length. Difficulties in LES begin with the challenge of providing accurate resolution of thin turbulent boundary layers at nozzle exit. Providing physi

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24

Bunnag, Shane. "Bleed Rate Model Based on Prandtl-Meyer Expansion for a Bleed Hole Normal to a Supersonic Freestream." University of Cincinnati / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1282330691.

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25

"The Supersonic Performance of High Bypass Ratio Turbofan Engines with Fixed Conical Spike Inlets." Master's thesis, 2018. http://hdl.handle.net/2286/R.I.49114.

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abstract: The objective of this study is to understand how to integrate conical spike external compression inlets with high bypass turbofan engines for application on future supersonic airliners. Many performance problems arise when inlets are matched with engines as inlets come with a plethora of limitations and losses that greatly affect an engine’s ability to operate. These limitations and losses include drag due to inlet spillage, bleed ducts, and bypass doors, as well as the maximum and minimum values of mass flow ratio at each Mach number that define when an engine can no longer function

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26

Panthi, Niraj. "Shock Dynamics due to Downstream Pressure Perturbations: Idealization of Transonic Unstarted Cascade Flutter." Thesis, 2019. https://etd.iisc.ac.in/handle/2005/4723.

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Shock wave unsteadiness is an important phenomenon in high-speed aerodynamics. This phenomenon is observed in many locations of high-speed vehicles, such as supersonic inlets, ramjet engines, transonic airfoils, high-speed fans, and compressors. In supersonic inlets and ramjet engines, unsteady shock motions can lead to large undesirable local fluctuations in properties such as pressure and heat transfer rate, besides overall thrust fluctuations. Shock unsteadiness in transonic airfoils can induce structural vibrations known as buffeting, while in gas turbine fans/compressors, shock osci

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27

Wu, Bor-Jing, and 吳伯軍. "The Numerical Analysis of the Flow Field in a Supersonic Inlet." Thesis, 1995. http://ndltd.ncl.edu.tw/handle/78306941039913436624.

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碩士<br>淡江大學<br>機械工程研究所<br>83<br>Since 1947, the human being first penetrated the sound barrier and get into the field of supersonic flight, it is more important for us to fly with supersonic speed, so the scientists of the world have doing their best to develop the supersonic vehicle and trying to upgrade their performance. the inlet is an important mechanism for a airbreathing supersonic vehicle, it must ensure the compressor to operate stably in any kind of situation and to decelerate the air in the inlet for the conpressor can handle. the purpose of this paper is using a numerical method t

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28

WU, LONG-NAN, and 吳龍男. "Numerical simulation of strong oblique shock/boundary layers interaction within a supersonic inlet." Thesis, 1991. http://ndltd.ncl.edu.tw/handle/28660059442204379241.

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29

(6632393), Ian Avalon Hall. "Simulating Scramjet Behavior: Unstart Prediction in a Supersonic, Turbulent Inlet-Isolator Duct Flow." Thesis, 2019.

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In the pursuit of developing hypersonic cruise vehicles, unstart is a major roadblock to achieving stable flight. Unstart occurs when a sudden instability in the combustor of a vehicle’s propulsion system creates an instantaneous pressure rise that initiates a shock. This shock travels upstream out of the inlet of the vehicle, until it is ejected from the inlet and creates a standing shockwave that chokes the flow entering the vehicle, thereby greatly reducing its propulsive capability. In severe cases, this can lead to the loss of the vehicle. This thesis presents the results of a computation

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30

PENG, JIAN-WEN, and 彭健文. "Numerical simulation for forebody/inlet integration flowfield of supersonic tactical missile using PNS methods." Thesis, 1991. http://ndltd.ncl.edu.tw/handle/54420097896512841538.

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31

Mahapatra, Debabrata. "Investigation Of Ramp/Cowl Shock Interaction Processes Near A Generic Scramjet Inlet At Hypersonic Mach Number." Thesis, 2008. https://etd.iisc.ac.in/handle/2005/807.

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One of the major technological innovations that are necessary for faster and cheaper access-to-space will be the commercial realization of supersonic combustion jet engines (SCRAMJET). The establishment of the flow through the inlet is one the prime requirement for the success of a SCRAMJET engine. The flow through a SCRAMJET inlet is dominated by inviscid /viscous coupling, transition, shock-shock interaction, shock boundary layer interaction, blunt leading edge effects and flow profile effects. Although the literature is exhaustive on various aspects of flow features associated with SCRAMJET

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32

Mahapatra, Debabrata. "Investigation Of Ramp/Cowl Shock Interaction Processes Near A Generic Scramjet Inlet At Hypersonic Mach Number." Thesis, 2008. http://hdl.handle.net/2005/807.

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One of the major technological innovations that are necessary for faster and cheaper access-to-space will be the commercial realization of supersonic combustion jet engines (SCRAMJET). The establishment of the flow through the inlet is one the prime requirement for the success of a SCRAMJET engine. The flow through a SCRAMJET inlet is dominated by inviscid /viscous coupling, transition, shock-shock interaction, shock boundary layer interaction, blunt leading edge effects and flow profile effects. Although the literature is exhaustive on various aspects of flow features associated with SCRAMJET

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