Numerical and experimental investigation of hypersonic streamwise vortices and their effect on mixing

Gomez, Llobet; Ramón, Juan

doi:10.14264/uql.2018.190

Cited by 2 publications

(6 citation statements)

References 82 publications

(213 reference statements)

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“…of 0.48. This vortex intensity is very similar to the values found in simulations of 2D scramjet geometries tested in T4 and the X3 expansion tube at UQ (15,18) . The width of the model/plate was 220 mm, which was selected to reduce the potential of any three-dimensional effects reaching the measurement area.…”

Section: Injectorsupporting

confidence: 85%

“…Figure 3 shows the model used in the experimental campaign. To ensure the model creates representative vortices, the Q factor was used to extract the vortex core location, size (defined as the region with Q > 0.5 Q max at core ), and intensity from these simulations (15,18) . Setting the fin angle to 10 • , and simulating a geometry equivalent to Fig.…”

Section: T4 Reflected Shock Tube Tunnelmentioning

confidence: 99%

“…1, following the procedure from Schultz (24,30) , Figure 4. Stanton number for the TFHG's in the boundary layer measurement region (18) . Theoretical laminar and turbulent Stanton number values calculated with the Cebeci Boundary Layer Code (31) .…”

Section: (B)mentioning

confidence: 99%

“…For this reason, the uncertainty was calculated by comparing the average heat flux value measured from multiple TFHGs during a fuel off flat plate configuration experiment (no injection and fin removed). The resulting TFHG 95% confidence interval is ±30%, calculated using t-Student distribution for a population of 10 gauges (18) . Figure 3(b) shows the TFHG sensor field that was employed to resolve the heat-transfer profile for the vortex-injection interaction.…”

Section: (B)mentioning

confidence: 99%

“…The largest mixing rate enhancements correspond to injection approximately half way between the vortex core and the separation line created by the SWBLI (16) . In their numerical studies, Llobet et al used a canonical geometry consisting of a flat plate and a compression wall, which can generate vortices representative of 2-D and 3-D shape transitioning inlets (17,18) The aim of the current work is to replicate the geometry of these prior works in experiment, to collect heat transfer data downstream of the vortex-injection interaction, and to benchmark prior numerical studies by providing corresponding experimental data.…”

Section: Introductionmentioning

confidence: 99%

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Experimental and numerical heat transfer from vortex-injection interaction in scramjet flowfields

et al. 2020

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Air-breathing propulsion has the potential to decrease the cost per kilogram for access-to-space, while increasing the flexibility of available low earth orbits. However, to meet the performance requirements, fuel-air mixing inside of scramjet engines and thermal management still need to be improved. An option to address these issues is to use intrinsically generated vortices from scramjet inlets to enhance fuel-air mixing further downstream, leading to shorter, less internal drag generating, and thus more efficient engines. Previous works have studied this vortex-injection interaction numerically, but validation was impractical due to lack of published experimental data. This paper extends upon these previous works by providing experimental data for a canonical geometry, obtained in the T4 Stalker Tube at Mach 8 flight conditions, and assesses the accuracy of numerical methodologies such as RANS CFD to predict the vortex-injection interaction. Focus is placed on understanding the ability of the numerical methodology to replicate the most important aspects of the vortex-injection interaction. Results show overall good agreement between the numerical and experimental results, as all major features are captured. However, limitations are encountered, especially due to a localised region of over predicted heat flux.

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Section: Injectorsupporting

confidence: 85%

Section: T4 Reflected Shock Tube Tunnelmentioning

confidence: 99%

Section: (B)mentioning

confidence: 99%

Section: (B)mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Experimental and numerical heat transfer from vortex-injection interaction in scramjet flowfields

et al. 2020

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Free-jet testing of a Mach 12 scramjet in an expansion tube

Toniato¹

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Scramjet technology has the theoretical potential to provide air-breathing propulsion as a more efficient alternative to conventional rocket propulsion. Since the vehicle captures its oxidiser from the atmosphere -as opposed to carrying it like a rocket -the specific impulse can theoretically be increased by an order of magnitude, thereby increasing payload mass fractions. In this context, threestage hybrid rocket-scramjet-rocket launch systems have shown to potentially provide a cost-effective and flexible solution for satisfying the requirements of the small-satellites market. However, to be economically feasible, the proposed scramjet-powered second stage would be reusable.Rectangular-to-Elliptical-Shape-Transitioning (REST) engines have shown to be a viable concept that can be integrated into access-to-space vehicles operating between Mach 5 and 12. The half-scale Mach 12 REST engine is a research scramjet specifically designed to operate in the last part of the ascent trajectory. Previous studies have demonstrated the ability of this design to successfully operate at equivalent flight conditions of Mach 11.6, 30 kPa dynamic pressure. However, tests have never been performed in freejet mode at the design conditions, as the facility which was used -the T4 reflected shock tunnel -was limited, like all RSTs by the extreme total pressure requirements of a Mach 12 flight. These limitations are aggravated by the even higher pressure necessary for pressure-length scaling, used to conserve the flow similarity between the half-scale experimental model and the flight engine.To overcome these limitations and allow freejet testing with pressure-length scaling, the use of expansion tubes has been proposed. These are currently the only kind of facility capable of producing these high-pressure requirements. Currently, the University of Queensland operates the X3 expansion tube, which is one of the few facilities worldwide with the potential to produce both the required total pressures and sufficiently long test times (up to 1.5 ms) to test an engine such as the Mach 12 REST engine.

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Numerical and experimental investigation of hypersonic streamwise vortices and their effect on mixing

Cited by 2 publications

References 82 publications

Experimental and numerical heat transfer from vortex-injection interaction in scramjet flowfields

Experimental and numerical heat transfer from vortex-injection interaction in scramjet flowfields

Free-jet testing of a Mach 12 scramjet in an expansion tube

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