Experiments on Shock-Boundary Layer Interaction and Cooling Efficiency in a Transpiration Cooled Model Scramjet

Strauss, Friedolin; Witte, Jan; Weißwange, Matthias; Manfletti, Chiara; Schlechtriem, Stefan

doi:10.2514/6.2017-4833

Cited by 16 publications

(7 citation statements)

References 17 publications

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“…However, for modern micro-porous materials, discrete gauges are likely to disturb the coolant outflow distribution and a non-intrusive measurement technique is highly desirable. In more recent years, low speed infrared thermography has been employed in long duration, supersonic facilities [5,9] but, additionally, testing in short duration hypersonic tunnels is desirable.…”

Section: Introductionmentioning

confidence: 99%

Transpiration-Cooling Heat Transfer Experiments in Laminar and Turbulent Hypersonic Flows

Naved¹,

Hermann²,

Hambidge³

et al. 2023

Journal of Thermophysics and Heat Transfer

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The design of a transpiration cooled system requires detailed local heat transfer information on and in the vicinity of the porous injector; however, limited spatially resolved experimental studies exist, particularly in hypersonic flows. In this work experiments were conducted in the Oxford High Density Tunnel at Mach 6.1 in both laminar and turbulent regimes. Spatially resolved 2D surface heat transfer measurements were acquired by imaging directly on and downstream of two micro-porous transpiration cooled injectors (METAPOR CE170 and Zirconia) using high-speed infra-thermography. Whilst injection in the laminar regime results in a steady, monotonic reduction in heat transfer from the start of the injector, a flatter profile is present for the turbulent cases where turbulent mixing inhibits surface heat transfer reduction.

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Section: Introductionmentioning

confidence: 99%

Transpiration-Cooling Heat Transfer Experiments in Laminar and Turbulent Hypersonic Flows

Naved¹,

Hermann²,

Hambidge³

et al. 2023

Journal of Thermophysics and Heat Transfer

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“…with density ρ and velocity u. Studies are excluded where the Reynolds number or blowing ratio could not be inferred from the published data [8,[29][30][31][32][33], or where other geometries were used [4,7,14,[34][35][36][37][38][39].…”

Section: Introductionmentioning

confidence: 99%

Performance of Transpiration-Cooled Heat Shields for Reentry Vehicles

2020

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This paper presents results of a system study of transpiration cooled thermal protection systems for Earth re-entry. The cooling performance for sustained hypersonic flight and transient re-entry of a blunt cone geometry is assessed. A simplified numerical model is used to calculate the transient temperature of a transpiration cooled heat shield. The performance of transpiration cooling is assessed by calculating the overall required coolant mass for different steady state and transient flight scenarios. Spatially and temporally optimised mass injection is presented for various flight conditions. The majority of the injection is required on the spherical nose segment of the blunted cone. Carbon/Carbon composite ceramic and the ultra high temperature ceramic Zirconium diboride are considered as wall materials. Both materials require similar amounts of coolant injection. In continuous hypersonic cruise, transpiration cooling is highly effective for flight conditions with velocities below 8 km s −1 and altitudes above 40 km. For transient re-entry, transpiration cooling is most viable for trajectories of entry velocities below 8.5 km s −1 and ballistic coefficients below 2.1 kg m −2. Nomenclature A Area, m 2 C D Drag coefficient c p Specific heat capacity, J kg −1 K −1

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“…The experiments were conducted at the high-speed air breathing propulsion test facility M11.1 of DLR's Institute of Space Propulsion at the site of Lampoldshausen. This test bench is equipped with sensitive Schlieren systems as well as high speed cameras to investigate supersonic flows (see Strauss et al, 2016Strauss et al, , 2017, for details). In the scientific field of aerospace applications with supersonic flows Schlieren photography is well-established and a standard non-intrusive measurement method.…”

Section: Recordings and Preprocessingmentioning

confidence: 99%

A corpus of Schlieren photography of speech production: potential methodology to study aerodynamics of labial, nasal and vocalic processes

Tomaschek

Arnold

Sering

et al. 2021

Lang Resources & Evaluation

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This report presents a corpus of articulations recorded with Schlieren photography, a recording technique to visualize aeroflow dynamics for two purposes. First, as a means to investigate aerodynamic processes during speech production without any obstruction of the lips and the nose. Second, to provide material for lecturers of phonetics to illustrates these aerodynamic processes. Speech production was recorded with 10 kHz frame rate for statistical video analyses. Downsampled videos (500 Hz) were uplodad to a youtube channel for illustrative purposes. Preliminary analyses demonstrate potential in applying Schlieren photography in research.

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Experiments on Shock-Boundary Layer Interaction and Cooling Efficiency in a Transpiration Cooled Model Scramjet

Cited by 16 publications

References 17 publications

Transpiration-Cooling Heat Transfer Experiments in Laminar and Turbulent Hypersonic Flows

Transpiration-Cooling Heat Transfer Experiments in Laminar and Turbulent Hypersonic Flows

Performance of Transpiration-Cooled Heat Shields for Reentry Vehicles

A corpus of Schlieren photography of speech production: potential methodology to study aerodynamics of labial, nasal and vocalic processes

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