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 :
Languages : en
Pages : 72
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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:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 850
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Book Description
Author: Michael J. Wright
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
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Book Description
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: Thomas D. Magruder
Publisher:
ISBN:
Category :
Languages : en
Pages : 354
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Book Description
Author: National Aeronautics and Space Adm Nasa
Publisher:
ISBN: 9781730766190
Category :
Languages : en
Pages : 66
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Book Description
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...
Author: Juergen W. Heberle
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 76
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Book Description
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.
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).
