This paper presents the design of an efficient, short-length shape transition inlet for hypersonic propulsion systems, operating at Mach 4 to 6. The inlet was shortened by approximately 24 % using a Busemann flow based on the median operating Mach number for streamline-tracing instead of the maximum operating Mach number. Additional upper circular arc of capture shape resulted in a compact compression surface that well preserves internal compression of the Busemann flow, and increased pressure rise by up to 31 % with higher total pressure recovery. The inlet was notched for maximum operating Mach number to minimize air spillage, and the range of operating Mach number and angle of attack was extended. Viscous effects were compensated by a proper truncation angle in order to maintain the exact circular throat shape for efficient manufacturing. The length-reduced inlet showed a wide operating range and high compression performance.
Sangwook Jin is a Ph.D. candidate in the Department of Aerospace Engineering of KAIST. He is currently a Senior Researcher at the Agency for Defense Development. His research interests include hypersonic air-breathing propulsion systems and high-enthalpy ground tests.
Hypersonic Air Breathing Propulsion Heiser 11.pdf
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These general requirements for all air-breathing engine inlets would place particular emphasis on some of the stated functions or others, depending on the specific characteristics of the propulsion system used and the vehicle mission. Some of these requirements are of general applicability; minimum pressure losses and least possible drag induction fall into this category. Other inlet characteristics have more or less significant influence, depending on the particular engine used. For example, dynamic distortions induced by an inlet can create serious difficulties for a gas-turbine-engine compressor because they reduce the stall margin, thus limiting the operational range. The extent to which the dynamic distortions affect a scramjet engine operation, on the other hand, is not entirely clear because increased flow unsteadiness could accelerate mixing but may also have a negative effect on momentum losses. This is not the case for the steady-state flow nonuniformities that have been shown to cause significant effects on the scramjet flow field, as they do on other engines.
Rocket and air-breathing propulsion systems are the foundation on which planning for future aerospace systems rests. A Review of United States Air Force and Department of Defense Aerospace Propulsion Needs assesses the existing technical base in these areas and examines the future Air Force capabilities the base will be expected to support. This report also defines gaps and recommends where future warfighter capabilities not yet fully defined could be met by current science and technology development plans. be457b7860
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