Topic
Shock diamond
About: Shock diamond is a research topic. Over the lifetime, 957 publications have been published within this topic receiving 16841 citations. The topic is also known as: Mach diamond.
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TL;DR: In this paper, a review of the fundamental characteristics of the shock train and pseudo-shock is presented, and some simple predictions are made to simulate these very complicated phenomena, and control methods of the pseudo-shocks are also described.
478 citations
TL;DR: In this article, the authors derived a scaling formula that the intensity of shock associated noise varies as (Mj2 − Md2)2 where Mj and Md are the fully expanded jet operating Mach number and nozzle design Mach number, respectively.
371 citations
TL;DR: In this paper, wall pressure fluctuations have been measured in a two-dimensional separated compression ramp-induced shock wave turbulent boundary-layer interaction at a nominal freestream Mach number of 3 and at Reynolds numbers based on boundary layer thickness of 78 X 10 and 14x 10.
Abstract: Wall pressure fluctuations have been measured in a two-dimensional separated compression ramp-induced shock wave turbulent boundary-layer interaction The tests were made at a nominal freestream Mach number of 3 and at Reynolds numbers based on boundary-layer thickness of 78 X 10 and 14x 10 The wall temperature condition was approximately adiabatic Large-amplitude pressure fluctuations exist throughout the interaction, particularly near separation and reattachment In the upstream region of the flowfield, the unsteadiness of the separation shock wave structure generates an intermittent wall pressure signal Mean wall pressures in this region result from the superposition of the relatively low-frequency, large-amplitude, shock wave-induced fluctuations on the pressure signal of the undisturbed boundary layer This behavior is qualitatively similar to that observed in three-dimensional blunt fin-induced flows In these two flowfields, the length scale of the shock motion is a significant fraction of the distance from the interaction start to separation
333 citations
TL;DR: In this article, the authors focused on the analytical prediction of the behavior of gaseous jets issuing transversely through a surface into an otherwise uniform stream, and focused upon the case of a supersonic main stream.
Abstract: This paper is concerned with the analytical prediction of the behavior of gaseous jets issuing transversely through a surface into an otherwise uniform stream. Primary emphasis is placed upon the case of a supersonic main stream. The work falls into three major areas. First, the use of a "solid body" drag model to describe the jet trajectory is re-examined, extended to include a supersonic main stream, and modified to alleviate the most untenable of the assumptions common to previous work. With this, good agreement between experiment and theoretical prediction is achieved. Second, the important general case of "underexpande d" injection is treated. A new model is adopted to permit the analysis of this extremely complicated flow problem. Briefly stated, an analogy is made between this and the simpler and well-understood situation of an underexpanded jet issuing into a quiescent medium. The key to this model is the notion of an "effective back pressure." Lastly, the analysis developed is applied to a configuration study of a combustion chamber for a hypersonic ramjet with supersonic combustion on a representative flight trajectory.
280 citations
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01 Jan 2010
TL;DR: In this paper, the authors present a general linear solution for Supersonic Flow over a wave-shaped wall, which is based on the Prandtl-Glauert Rule for Subsonic Flow.
Abstract: Preface. About the Author. 1 Basic Facts. 1.1 Definition of Gas Dynamics. 1.2 Introduction. 1.3 Compressibility. 1.4 Supersonic Flow What is it? 1.5 Speed of Sound. 1.6 Temperature Rise. 1.7 Mach Angle. 1.8 Thermodynamics of Fluid Flow. 1.9 First Law of Thermodynamics (Energy Equation). 1.10 The Second Law of Thermodynamics (Entropy Equation). 1.11 Thermal and Calorical Properties. 1.12 The Perfect Gas. 1.13 Wave Propagation. 1.14 Velocity of Sound. 1.15 Subsonic and Supersonic Flows. 1.16 Similarity Parameters. 1.17 Continuum Hypothesis. 1.18 Compressible Flow Regimes. 1.19 Summary. Exercise Problems. 2 Steady One-Dimensional Flow. 2.1 Introduction. 2.2 Fundamental Equations. 2.3 Discharge from a Reservoir. 2.4 Streamtube Area Velocity Relation. 2.5 de Laval Nozzle. 2.6 Supersonic Flow Generation. 2.7 Performance of Actual Nozzles. 2.8 Diffusers. 2.9 Dynamic Head Measurement in Compressible Flow. 2.10 Pressure Coefficient. 2.11 Summary. Exercise Problems. 3 Normal Shock Waves. 3.1 Introduction. 3.2 Equations of Motion for a Normal Shock Wave. 3.3 The Normal Shock Relations for a Perfect Gas. 3.4 Change of Stagnation or Total Pressure Across a Shock. 3.5 Hugoniot Equation. 3.6 The Propagating Shock Wave. 3.7 Reflected Shock Wave. 3.8 Centered Expansion Wave. 3.9 Shock Tube. 3.10 Summary. Exercise Problems. 4 Oblique Shock and ExpansionWaves. 4.1 Introduction. 4.2 Oblique Shock Relations. 4.3 Relation between and . 4.4 Shock Polar. 4.5 Supersonic Flow Over a Wedge. 4.6 Weak Oblique Shocks. 4.7 Supersonic Compression. 4.8 Supersonic Expansion by Turning. 4.9 The Prandtl Meyer Expansion. 4.10 Simple and Nonsimple Regions. 4.11 Reflection and Intersection of Shocks and Expansion Waves. 4.12 Detached Shocks. 4.13 Mach Reflection. 4.14 Shock-Expansion Theory. 4.15 Thin Aerofoil Theory. 4.15.1 Application of Thin Aerofoil Theory. 4.16 Summary. Exercise Problems. 5 Compressible Flow Equations. 5.1 Introduction. 5.2 Crocco's Theorem. 5.3 General Potential Equation for Three-Dimensional Flow. 5.4 Linearization of the Potential Equation. 5.5 Potential Equation for Bodies of Revolution. 5.6 Boundary Conditions. 5.7 Pressure Coefficient. 5.8 Summary. Exercise Problems. 6 Similarity Rule. 6.1 Introduction. 6.2 Two-Dimensional Flow: The Prandtl-Glauert Rule for Subsonic Flow. 6.3 Prandtl Glauert Rule for Supersonic Flow: Versions I and II. 6.4 The von Karman Rule for Transonic Flow. 6.5 Hypersonic Similarity. 6.6 Three-Dimensional Flow: Gothert s Rule. 6.7 Summary. Exercise Problems. 7 Two-Dimensional Compressible Flows. 7.1 Introduction. 7.2 General Linear Solution for Supersonic Flow. 7.3 Flow Over a Wave-Shaped Wall. 7.4 Summary. Exercise Problems. 8 Flow with Friction and Heat Transfer. 8.1 Introduction. 8.2 Flow in Constant Area Duct with Friction. 8.4 Flow with Heating or Cooling in Ducts. 8.5 Summary. Exercise Problems. 9 Method of Characteristics. 9.1 Introduction. 9.2 The Concepts of Characteristic. 9.3 The Compatibility Relation. 9.4 The Numerical Computational Method. 9.5 Theorems for Two-Dimensional Flow. 9.6 Numerical Computation with Weak Finite Waves. 9.7 Design of Supersonic Nozzle. 9.8 Summary. 10 Measurements in Compressible Flow. 10.1 Introduction. 10.2 Pressure Measurements. 10.3 Temperature Measurements. 10.4 Velocity and Direction. 10.5 Density Problems. 10.6 Compressible Flow Visualization. 10.7 Interferometer. 10.8 Schlieren System. 10.9 Shadowgraph. 10.10 Wind Tunnels. 10.11 Hypersonic Tunnels. 10.12 Instrumentation and Calibration of Wind Tunnels. 10.13 Calibration and Use of Hypersonic Tunnels. 10.14 Flow Visualization. 10.15 Summary. Exercise Problems. 11 Ramjet. 11.1 Introduction. 11.2 The Ideal Ramjet. 11.3 Aerodynamic Losses. 11.4 Aerothermodynamics of Engine Components. 11.5 Flow Through Inlets. 11.6 Performance of Actual Intakes. 11.7 Shock Boundary Layer Interaction. 11.8 Oblique Shock Wave Incident on Flat Plate. 11.9 Normal Shocks in Ducts. 11.10 External Supersonic Compression. 11.11 Two-Shock Intakes. 11.12 Multi-Shock Intakes. 11.13 Isentropic Compression. 11.14 Limits of External Compression. 11.15 External Shock Attachment. 11.16 Internal Shock Attachment. 11.17 Pressure Loss. 11.18 Supersonic Combustion. 11.19 Summary. 12 Jets. 12.1 Introduction. 12.2 Mathematical Treatment of Jet Profiles. 12.3 Theory of Turbulent Jets. 12.4 Experimental Methods for Studying Jets and the Techniques Used for Analysis. 12.5 Expansion Levels of Jets. 12.6 Control of Jets. 12.7 Summary. Appendix. References. Index.
252 citations