Mach 10 Hypersonic Nozzle: Improved Flow Quality

Lacey, J.; Inoue, Yoshio; Higashida, Akio; Inoue, Manabu; Ishizaka, Kouichi; Korte, John J.

doi:10.2514/2.3925

Cited by 2 publications

(1 citation statement)

References 2 publications

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“…Some uses of CFD has been in the design of wind tunnel nozzles, [4][5][6] for understanding the flow in high-enthalpy facilities 7,8 and for understanding the effects of model blockage and model mounts. 9,10 The use of CFD for simulating the flow in an entire wind tunnel, particularly at low speeds, has also been reported.…”

Section: Introductionmentioning

confidence: 99%

Development of a Supersonic Aerodynamic Test Section Using Computational Modeling

Mitchell

Lu²

2009

39th AIAA Fluid Dynamics Conference

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The design of a supersonic aerodynamic test section was implemented using computational modeling. Initial two-dimensional computational flow simulations revealed critical design issues such as starting the test section and model placement. These issues were resolved to provide a test section capable of operating throughout the Mach number range of the tunnel, with reduced flow blockage and substantial optical access. The final test section inlet design, tunnel starting data and optical access are shown.

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Section: Introductionmentioning

confidence: 99%

Development of a Supersonic Aerodynamic Test Section Using Computational Modeling

Mitchell

Lu²

2009

39th AIAA Fluid Dynamics Conference

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Modern developments in hypersonic wind tunnels

Stalker¹

2006

Aeronaut. j.

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The development of new methods of producing hypersonic wind-tunnel flows at increasing velocities during the last few decades is reviewed with attention to airbreathing propulsion, hypervelocity aerodynamics and superorbital aerodynamics. The role of chemical reactions in these flows leads to use of a binary scaling simulation parameter, which can be related to the Reynolds number, and which demands that smaller wind tunnels require higher reservoir pressure levels for simulation of flight phenomena. The use of combustion heated vitiated wind tunnels for propulsive research is discussed, as well as the use of reflected shock tunnels for the same purpose. A flight experiment validating shock-tunnel results is described, and relevant developments in shock tunnel instrumentation are outlined. The use of shock tunnels for hypervelocity testing is reviewed, noting the role of driver gas contamination in determining test time, and presenting examples of air dissociation effects on model flows. Extending the hypervelocity testing range into the superorbital regime with useful test times is seen to be possible by use of expansion tube/tunnels with a free piston driver.

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Mach 10 Hypersonic Nozzle: Improved Flow Quality

Cited by 2 publications

References 2 publications

Development of a Supersonic Aerodynamic Test Section Using Computational Modeling

Development of a Supersonic Aerodynamic Test Section Using Computational Modeling

Modern developments in hypersonic wind tunnels

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