Experimental Investigation of Starting Process for a Variable Geometry Air Inlet operating from Mach 2 to Mach 8

Falempin, François; Wendling, Eric; Goldfeld, M. A.; Starov, A.

doi:10.2514/6.2006-4513

Cited by 30 publications

(11 citation statements)

References 4 publications

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“…The air-inlet starting in a wind tunnel can occur in different fashions depending on its type [9,10]. In the test section of a blow-down wind tunnel a vacuum is maintained before the starting.…”

Section: Modeling Supersonic Air-inlet Starting In a Blow-down Wind Tmentioning

confidence: 99%

Leading edge bluntness effect on the flow in a model air-inlet

et al. 2014

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Flow in an idealized air-inlet with plane walls and a rectangular cross-section is experimentally investigated. The air-inlet is mounted on a plate, at a distance well removed from its leading edge. The experiments were conducted in a Ludwig tube at M ∞ = 5 and Re ∞L = 23 × 10 6 and 13 × 10 6 . A panoramic (optical) technique of measuring the heat transfer coefficient is for the first time applied to study the internal flow in an air-inlet. The data on the effect of the bluntness of the leading edges of the plate and the air-inlet cowl on the heat transfer coefficient distribution and the flow structure within the air-inlet are obtained. It is shown that in an air-inlet with large channel constriction an even small bluntness of the plate or the cowl can lead to global changes in the flow structure.

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Section: Modeling Supersonic Air-inlet Starting In a Blow-down Wind Tmentioning

confidence: 99%

Leading edge bluntness effect on the flow in a model air-inlet

et al. 2014

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“…In effort to manage these problems, numerous methods including flow control [17,15,1], magnetohydrodynamic control [7,11,8] and variable geometry [13,20,3,4,14,9] have been proposed by researchers and developers. The primary goal of this body of research is to avoid hypersonic inlets plunging into unstart status, and to minimize flow spillage under off-design conditions.…”

Section: Introductionmentioning

confidence: 99%

Variable geometry cowl sidewall for improving rectangular hypersonic inlet performance

Teng

Yuan

2015

Aerospace Science and Technology

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“…By rotating the cowl lip at off-design points, Jin successfully reduced the starting Mach number to 3.5 for a hypersonic inlet designed at Mach 6 [3] . Falempin investigated a combined variable inlet/combustor cowl which could adapt the contraction ratio to the flight conditions from Mach 2 to 8 [4] . Zhang proposed a moveable slot-plate control method to solve hypersonic inlet unstart [5] .…”

Section: Introductionmentioning

confidence: 99%

Fluid Dynamic Analysis on the Adaptive Slot Method of Hypersonic Inlets

Zhu¹,

You²

2017

Proceedings of the 2017 2nd International Conference on Modelling, Simulation and Applied Mathematics (MSAM2017)

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To enhance the starting ability was one of the most serious issues in air propulsion system. In the present work, an adaptive slot control method was proposed to expand the working range of hypersonic inlets to a lower Mach number with weak losses, which was beneficial for engineering applications. Simulation results indicated that the starting Mach number can be decreased from 3.2 to 3.0 with five parallel slots at a width of 4mm. The flow inside the slot channel was self-driven due to the pressure gradient across of the separation shock. In case that the inlet was restart, the slot channel flow would be strongly suppressed.

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Experimental Investigation of Starting Process for a Variable Geometry Air Inlet operating from Mach 2 to Mach 8

Cited by 30 publications

References 4 publications

Leading edge bluntness effect on the flow in a model air-inlet

Leading edge bluntness effect on the flow in a model air-inlet

Variable geometry cowl sidewall for improving rectangular hypersonic inlet performance

Fluid Dynamic Analysis on the Adaptive Slot Method of Hypersonic Inlets

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