Development of Hypersonic Quiet Tunnels

Schneider, Steven P.

doi:10.2514/1.34489

Cited by 216 publications

(47 citation statements)

References 120 publications

(278 reference statements)

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“…Flow conditions can be found in [17]. For details on the design and development of hypersonic quiet tunnels, including the BAM6QT, see Reference [38]. The nozzle is highly polished to prevent roughnessinduced transition on the walls.…”

Section: Secondary Instability Of High-speed Crossflow Wavesmentioning

confidence: 99%

Secondary Instabilities of Hypersonic Stationary Crossflow Waves

Edelman

2018

AIAA Journal

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Section: Secondary Instability Of High-speed Crossflow Wavesmentioning

confidence: 99%

Secondary Instabilities of Hypersonic Stationary Crossflow Waves

Edelman

2018

AIAA Journal

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“…The flow parameters used for the simulations presented in this thesis are based on the experimental conditions of the Boeing/AFOSR Mach 6 Quiet Tunnel (BAM6QT)at Purdue university (Schneider, 2008(Schneider, , 2009). The BAM6QT can be operated as a conventional noisy tunnel or as a quiet tunnel and it is currently one of the two hypersonic quiet tunnels in the world.…”

Section: Flow Parameters and Physical Problemmentioning

confidence: 99%

Numerical Investigation of Laminar-Turbulent Transition in a Cone Boundary Layer at Mach 6

Sivasubramanian

2011

41st AIAA Fluid Dynamics Conference and Exhibit

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“…See the review by Schneider (2008) for a discussion of the influence of test flow noise on boundary layer transition. 3 The stated value is for low pressure shot 10927 relative to shot 10929.…”

Section: Fuel-off Datamentioning

confidence: 99%

An experimental investigation of an airframe integrated three-dimensional scramjet engine at a Mach 10 flight condition

Doherty¹

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The University of Queensland in 2014 school of mechanical and mining engineering centre for hypersonics abstract Realisation of the dream of airbreathing access-to-space requires the development of a scramjet engine that produces sufficient net thrust to enable acceleration over a wide Mach number range. With engines that are highly integrated with the airframe, the net performance of a scramjet powered vehicle is closely coupled with the vehicle attitude and is difficult to determine only from component level studies. This work investigates the influence of airframe integration on the performance of an airframe integrated scramjet through the measurement of internal pressure distribution and the direct measurement of the net lift, thrust and pitching moment using a three-component stress wave force balance. The engine chosen as the basis for this study was the Mach 12 rectangularto-elliptical shape-transition (m12rest) scramjet that was developed by Suraweera and Smart (2009) as a research engine for access-to-space applications. The inlet and combustor flowpath were integrated with a slender 6°wedge forebody, streamlined external geometry and three dimensional thrust nozzle. The scale of the engine was chosen so that the entire engine would fit within the core-flow diamond (bi-conic) produced by a Mach 10 facility nozzle. The Mach 10b facility nozzle was chosen because it is the largest nozzle current in use with the t4 Stalker Tube and because the offdesign performance of a scramjet engine is of interest for access-to-space vehicles that must accelerate over a range of Mach numbers.Freejet experiments were conducted within the t4 Stalker Tube. Two trueflight Mach 10 test conditions were used: a high pressure test condition that replicated flight at a dynamic pressure of 48 kPa and a low pressure test condition that replicated flight at a dynamic pressure of 28 kPa. Scaling of the test conditions according to the established binary scaling law was not completed due to facility operational limits.The engine featured two fuel injection stations from which gaseous hydrogen was injected. The first injection station was partway along the length of the inlet while the second injection station was at the start of the combustor behind a rearward facing circumferential step. In addition to investigating inlet-only and step-only injection, a combined scheme where 68 % of the fuel was injected from the step station and 32 % from the inlet station was also investigated.To support the analysis of the experimental results, numerical simulations of the engine with no fuel injection were conducted using the nasa code vulcan. Analysis of the simulations show that the mass capture ratio with respect to the projected inlet area is approximately 60 % at each test condition. The simulations also show that spillage of flow from the slender forebody accounts for just 12 % of the flow through the projected iii inlet area, a small but non-negligible fraction. By integrating the engine surface forces, the drag coefficient with respect ...

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Development of Hypersonic Quiet Tunnels

Cited by 216 publications

References 120 publications

Secondary Instabilities of Hypersonic Stationary Crossflow Waves

Secondary Instabilities of Hypersonic Stationary Crossflow Waves

Numerical Investigation of Laminar-Turbulent Transition in a Cone Boundary Layer at Mach 6

An experimental investigation of an airframe integrated three-dimensional scramjet engine at a Mach 10 flight condition

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