Effects of Leading-Edge Truncation and Stunting on Drag and Efficiency of Busemann Intakes for Axisymmetric Scramjet Engines

Hideaki Ogawa, Sannu Mölder, Russell Boyce

Research output: Contribution to journalArticle

Abstract

Designing high-performance air intakes is of crucial importance for the successful operation of hypersonic scramjet propulsion. This paper investigates the performance of axisymmetric intakes obtained by applying two shortening methods, namely, leading-edge truncation and stunting (longitudinal contraction), to the full Busemann intake in inviscid and viscous flowfields. The primary aim is to identify the key design factors and underlying flow physics in order to achieve the optimum performance with minimum weight by striking the balance between viscous and shock losses. The effects of intake shortening on performance are similar for the two methods for moderate length reduction (25%), conducing to considerable reduction in intake weight. Even reduced to half length, truncated intakes can produce reasonable compression (60% of the full Busemann intake) with the original level of total pressure recovery maintained in viscous flowfields. Stunted intakes, on the other hand, can enhance compression with considerable total pressure penalty, eventually leading to intake unstart at a certain point due to the emergence of Mach reflection, which makes this method potentially useful in situations where locally high pressure and temperature are desired near the centreline at the cost of total pressure recovery.
Original languageEnglish
Pages (from-to)186-199
JournalJournal of Fluid Science and Technology
Volume8
Issue number2
Publication statusPublished - 2013

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Drag
Engines
Recovery
Air intakes
Hypersonic aerodynamics
Propulsion
Mach number
Physics
Temperature

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Effects of Leading-Edge Truncation and Stunting on Drag and Efficiency of Busemann Intakes for Axisymmetric Scramjet Engines. / Ogawa, Hideaki; Mölder, Sannu; Boyce, Russell.

In: Journal of Fluid Science and Technology, Vol. 8, No. 2, 2013, p. 186-199.

Research output: Contribution to journalArticle

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