Experimental Studies of Shock Interaction Phenomena Associated with Hypersonic Airbreathing Propulsion

Abstract

REPORT DOCUMENTATION PAGE tidf.Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instnjctions, searching existing data sources, gathenng and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports. 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. and 168 ABSTRACT (Maximum 200 words)Experimental studies were conducted in conjunction with computations in a code validation exercise to exarrne the ability of DSMC and Navier-Stokes techniques to predict the complex characteristics of regions of shock/shock and shock/ be. .däry layer interactions in hypervelocity flows. In the experimental program, detailed heat transfer and pressure measurements in larr iar regions of shock wave/boundary layer interaction, and shock/shock interaction, over hollow cylinder/flare and double ecu« configurations in hypersonic flow. In the best Navier-Stokes solutions the structure and density of the fiowfield was captured exactly over both the hollow cylinder/flare and double cone models. The detailed characteristics of the distribution of pressure and heating through the interaction regions were well predicted. In general, for these relatively high-density flows, the DSMC solutions did not capture the characteristics of well-separated flows. In Part 2 of this program, experimental studies have been conducted in the LENS I shock tunnel to investigate the characteristics and performance of full-scale scramjet engines at fully duplicated flight conditions for a range of dynamic pressures at Mach 7. In this program we obtained detailed heat transfer and pressure measurements together with high speed Schlieren and infrared imagery to determine the characteristics of a generic engine, the flow path of which was configured to be similar to the Air Force Hy-Tech configuration for studies with hydrocarbon and hydrogen fuels.14. SUBJECT TERMS CFD code validation; laminar shock boundary layer interaction; shock/shock interaction; heat transfer and pressure measurements; fiowfield characteristics; scramjet engine AbstractExperimental studies were conducted in conjunction with computations in a code validation exercise to examine the ability of DSMC and Navier-Stokes techniques to predict the complex characteristics of regions of shock/shock and shock/ boundary layer interactions in hypervelocity flows. In the experimental program, detailed heat transfer and pressure measurements were made in laminar regions of shock wave/boundary layer interaction and shock/shock interaction over hollow cylinder/flare and double cone configurations in hypersonic flow. The experimental studies were conducted for a Mach number range from 10 to 12 with Reynolds numbers from 1 x 10 4 to 5 x 10 5 ...