Experimental Studies Of Shock Shock Interactions On A 9 Cone
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Experimental Studies of Shock-shock Interactions on a 9° Cone by David L. Merritt Pdf
A ballistics range and a shocktube were used to study head-on interactions between 9-degree cones flying at supersonic speeds and plane shock waves. Photographs of the shock-shock interaction were taken. Experimental shock wave patterns agreed with predicted patterns. The reflected shock wave produced little or no overpressure on the model. (Author).
Oblique Shock Interaction Experiments by David L. Merritt,Philip M. Aronson Pdf
A description is given of a unique experimental technique for simulating the interaction between a re-entry vehicle and an oblique blast wave. The technique combines a ballistics range with a shocktube. Models fly down the range and through the shocktube at an oblique angle. As a model passes through the shocktube, it intercepts a plane shock wave moving down the tube. Sequential photographs show the interaction between the model and the shock wave. Experiments were done with 9- and 15-degree half-angle cone models. The Mach numbers of both the models and the shock waves ranged from 2 to 5. The peak transient pressure on the model resulting from the reflection of the shock wave was calculated using data measured from the photographs. The analysis technique was verified by direct measurements of reflected shock pressures on a stationary cone model. (Author).
Further Evaluation of a Telemetry System for Use in Shock Interaction Experiments by David L. Merritt,Philip M. Aronson Pdf
The feasibility of using the Lockheed Miniature High 'G' Telemetry System to measure transient pressures on a model flying through a head-on shock wave was investigated previously in the NOL Shock Interaction Range. An additional brief test program was run to see if there are any special problems associated with the use of the same telemetry system for oblique shock interaction experiments. Three nine-degree half-angle cone models, each equipped with a capacitance-type pressure gage and a single channel FM transmitter, were launched from a 40mm powder gun at a speed of 2600 fps. The models flew through a Mach 3 shock wave which was oriented at a 50-degree angle to the flight path of the models. Signals were received from two of the models. As in the earlier tests, the pressure gage was found to need improvement in both frequency response and damping characteristics. An in-flight calibration technique is also needed. The only new problem area uncovered that is specifically associated with oblique interaction tests is model-roll control. (Author).
Evaluation of a Telemetry System for Use in Shock Interaction Experiments by David L. Merritt,Philip M. Aronson Pdf
The ability of the Miniature Telemetry System to measure transient pressures on a model flying through a shock wave was investigated in the NOL Shock Interaction Range. Ten instrumented models were flown. (Author).
Shock Interaction Surface Pressures for Hemispherical and Conical Bodies by Frank P. Baltakis Pdf
Transient pressures, induced by wind-tunnel simulated head-on blast wave interactions, have been measured on a hemisphere and on cones of 9-, 15- and 30-degree semivertex angles. Blast wave Mach numbers of 1.6 to 2.2, 2.2 to 5.85 and 2.7 to 4.4 were simulated at the free-stream Mach numbers of 3.1, 5.1 and 7, respectively. Measured pressure-time histories for the hemisphere were compared and found in agreement with histories predicted by McNamara's FLAME code. Peak overpressures for the cones were tested for agreement with values predicted by a simple theoretical method in which an assumption is made that the blast wave forms a Mach stem moving along the surface at a velocity whose axial component equals the velocity of the main blast wave. The effects of angle of attack and of nose blunting were also investigated with the nine-degree cone at a free-stream Mach number of 5.1. (Author).
Experimental Studies of Hypersonic Shock-Wave Boundary-Layer Interactions by National Aeronautics and Space Adm Nasa Pdf
Two classes of shock-wave boundary-layer interactions were studied experimentally in a shock tunnel in which a low Reynolds number, turbulent flow at Mach 8 was developed on a cold, flat test surface. The two classes of interactions were: (1) a swept interaction generated by a wedge ('fin') mounted perpendicularly on the flat plate; and (2) a two-dimensional, unseparated interaction induced by a shock impinging near an expansion corner. The swept interaction, with wedge angles of 5-20 degrees, was separated and there was also indication that the strongest interactions prossessed secondary separation zones. The interaction spread out extensively from the inviscid shock location although no indication of quasi-conical symmetry was evident. The surface pressure from the upstream influence to the inviscid shock was relatively low compared to the inviscid downstream value but it rose rapidly past the inviscid shock location. However, the surface pressure did not reach the downstream inviscid value and reasons were proposed for this anomalous behavior compared to strongly separated, supersonic interactions. The second class of interactions involved weak shocks impinging near small expansion corners. As a prelude to studying this interaction, a hypersonic similarity parameter was identified for the pure, expansion corner flow. The expansion corner severely damped out surface pressure fluctuations. When a shock impinged upstream of the corner, no significant changes to the surface pressure were found as compared to the case when the shock impinged on a flat plate. But, when the shock impinged downstream of the corner, a close coupling existed between the two wave systems, unlike the supersonic case. This close coupling modified the upstream influence. Regardless of whether the shock impinged ahead or behind the corner, the downstream region was affected by the close coupling between the shock and the expansion. Not only was the mean pressure distribution modified but the un...
Shock Wave-Boundary-Layer Interactions by Holger Babinsky,John K. Harvey Pdf
Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines. SBLIs have the potential to pose serious problems in a flowfield; hence they often prove to be a critical - or even design limiting - issue for many aerospace applications. This is the first book devoted solely to a comprehensive, state-of-the-art explanation of this phenomenon. It includes a description of the basic fluid mechanics of SBLIs plus contributions from leading international experts who share their insight into their physics and the impact they have in practical flow situations. This book is for practitioners and graduate students in aerodynamics who wish to familiarize themselves with all aspects of SBLI flows. It is a valuable resource for specialists because it compiles experimental, computational and theoretical knowledge in one place.
Experimental Methods of Shock Wave Research by Ozer Igra,Friedrich Seiler Pdf
This comprehensive and carefully edited volume presents a variety of experimental methods used in Shock Waves research. In 14 self contained chapters this 9th volume of the “Shock Wave Science and Technology Reference Library” presents the experimental methods used in Shock Tubes, Shock Tunnels and Expansion Tubes facilities. Also described is their set-up and operation. The uses of an arc heated wind tunnel and a gun tunnel are also contained in this volume. Whenever possible, in addition to the technical description some typical scientific results obtained using such facilities are described. Additionally, this authoritative book includes techniques for measuring physical properties of blast waves and laser generated shock waves. Information about active shock wave laboratories at different locations around the world that are not described in the chapters herein is given in the Appendix, making this book useful for every researcher involved in shock/blast wave phenomena.
30th International Symposium on Shock Waves 2 by Gabi Ben-Dor,Oren Sadot,Ozer Igra Pdf
These proceedings collect the papers presented at the 30th International Symposium on Shock Waves (ISSW30), which was held in Tel-Aviv Israel from July 19 to July 24, 2015. The Symposium was organized by Ortra Ltd. The ISSW30 focused on the state of knowledge of the following areas: Nozzle Flow, Supersonic and Hypersonic Flows with Shocks, Supersonic Jets, Chemical Kinetics, Chemical Reacting Flows, Detonation, Combustion, Ignition, Shock Wave Reflection and Interaction, Shock Wave Interaction with Obstacles, Shock Wave Interaction with Porous Media, Shock Wave Interaction with Granular Media, Shock Wave Interaction with Dusty Media, Plasma, Magnetohyrdrodynamics, Re-entry to Earth Atmosphere, Shock Waves in Rarefied Gases, Shock Waves in Condensed Matter (Solids and Liquids), Shock Waves in Dense Gases, Shock Wave Focusing, Richtmyer-Meshkov Instability, Shock Boundary Layer Interaction, Multiphase Flow, Blast Waves, Facilities, Flow Visualization, and Numerical Methods. The two volumes serve as a reference for the participants of the ISSW30 and anyone interested in these fields.
Data on Shape and Location of Detached Shock Waves on Cones and Spheres by Juergen W. Heberle Pdf
Accurate experimental data are given on the shape and the location of detached shock waves on cones and spheres at Mach numbers from 1.17 to 1.81. The data are correlated to obtain equations that describe the shock waves. This knowledge of the shock waves should be useful in calculations of the pressure distribution and the pressure drag of the fore part of cones and spheres. The experimental data on shock waves are compared with theory.
Shock Wave Interactions by Konstantinos Kontis Pdf
This edited monograph contains the proceedings of the International Shock Interaction Symposium, which emerged as an heir to both the Mach Reflection and Shock Vortex Interaction Symposia. These scientific biannual meetings provide an ideal platform to expose new developments and discuss recent challenges in the field of shock wave interaction phenomena. The goal of the symposia is to offer a forum for international interaction between young and established scientists in the field of shock and blast wave interaction phenomena. The target audience of this book comprises primarily researchers and experts in the field of shock waves, but the book may also be beneficial for young scientists and graduate students alike.