Experimental Studies of Shock-shock Interactions on a 9° Cone PDF Download
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Author: David L. Merritt
Publisher:
ISBN:
Category : Ballistic ranges
Languages : en
Pages : 100
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Book Description
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).
Author: David L. Merritt
Publisher:
ISBN:
Category : Ballistic ranges
Languages : en
Pages : 100
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Book Description
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).
Author: David L. Merritt
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 148
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Book Description
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).
Author: Frank P. Baltakis
Publisher:
ISBN:
Category : Guided missiles
Languages : en
Pages : 148
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Book Description
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).
Author: David L. Merritt
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 70
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Book Description
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).
Author: Holger Babinsky
Publisher: Cambridge University Press
ISBN: 1139498649
Category : Technology & Engineering
Languages : en
Pages : 481
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Book Description
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.
Author: Ozer Igra
Publisher: Springer
ISBN: 3319237454
Category : Technology & Engineering
Languages : en
Pages : 480
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Book Description
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.
Author: David L. Merritt
Publisher:
ISBN:
Category : Aerospace telemetry
Languages : en
Pages : 72
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Book Description
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).
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 850
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1006
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Book Description
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 636
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Book Description
