Modeling and Simulation of Bleed Holes in the Presence of Shock Wave/Boundary Layer Interaction

Orkwis, Paul D.; Turner, Mark G.; Apyan, Alex; Flenar, Kyle; Duncan, Sean; Wukie, Nathan A.

doi:10.2514/6.2013-425

Cited by 7 publications

(6 citation statements)

References 7 publications

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“…al., 11 Hamed et al 12 and Orkwis et. al., 13 explored both simulations and models based on the Slater approach. These efforts have found that surface boundary conditions alone have great difficulty providing accurate bleed predictions that include both mass removal and the subsequent downstream flow effect.…”

Section: B Previous Workmentioning

confidence: 99%

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Comparison of Experimental and Computational Flow Structure Investigations of a Normal-Hole Bled Supersonic Boundary Layer

Oorebeek

Babinsky

Ugolotti

et al. 2014

32nd AIAA Applied Aerodynamics Conference

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A series of experiments have been conducted on an array of bleed holes spanning the width of the CUED supersonic wind tunnel at Mach numbers of 1.8 and 2.5. The wind tunnel was run with varying levels of suction, and the resulting flow structure over the bleed array was subsequently mapped with a Laser Doppler Velocimetry (LDV) system at a resolution of 0.25 hole diameters or better. The same wind tunnel setup was also simulated using the OVERFLOW Navier-Stokes equation solver. Overall good agreement was found in the definition of the expansion fan and barrier shock pattern produced by flow entering the normal holes, with the production of streamwise vorticity noted in both CFD and experimental studies. The proposed mechanism of vorticity generation is an effect of the barrier shock standing off from the rear edge of each bleed hole, and is predicted by CFD to increase in strength as Mach number increases, as well as when the vorticity is produced by a single hole, rather than an array. Both studies found that vorticity decreases as suction strength is reduced, however the experimental study showed the vortices persist farther downstream than predicted by CFD.

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Section: B Previous Workmentioning

confidence: 99%

“…13 Experiments and computations will be run with Mach 1.8 and 2.5 flow over a bleed region comprising of 2mm diameter normal holes, a setup applicable to performance bleed in mixed compression inlets. The goal is to better develop the CFD modeling tools, and validate the computational results with experimental data.…”

Section: Current Researchmentioning

confidence: 99%

Comparison of Experimental and Computational Flow Structure Investigations of a Normal-Hole Bled Supersonic Boundary Layer

Oorebeek

Babinsky

Ugolotti

et al. 2014

32nd AIAA Applied Aerodynamics Conference

View full text Add to dashboard Cite

show abstract

“…For these simulations, the Harten-Lax-van Leer-Contact flux scheme, shear stress transport (SST) turbulence model, Koren flux limiter, and a third-order spatial discretization were used. Previous simulations of similar cases [13] had used the SST turbulence model to provide convergent analysis and reliable results, and thus it was retained for this work.…”

Section: Simulation and Modeling Techniques 1 Flow Solver And Boumentioning

confidence: 99%

“…al. [13] explored both simulations and models based on the Slater approach from [7]. These efforts have found that surface boundary conditions alone have great difficulty providing accurate bleed predictions that include both mass removal and the subsequent downstream flow effect.…”

mentioning

confidence: 99%

“…To better develop models of bleed for flow control in inlets, this paper continues the experimental study started at the University of Cambridge [21], combining it with high-resolution computational fluid dynamics (CFD) from the University of Cincinnati [13]. Experiments and computations were run with Mach 1.8 and 2.5 flow over a bleed region composed of 2-mm-diam normal holes, a setup applicable to performance bleed in mixed compression inlets.…”

mentioning

confidence: 99%

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Experimental and Computational Investigations of a Normal-Hole-Bled Supersonic Boundary Layer

Oorebeek¹,

Babinsky²,

Ugolotti³

et al. 2015

AIAA Journal

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A series of experiments have been conducted on a bleed hole array spanning the width of the Cambridge University Engineering Department supersonic wind tunnel at Mach numbers of 1.8 and 2.5. The wind tunnel was run with varying levels of suction, and the flow structure over the bleed array was subsequently mapped with a laser Doppler velocimetry system at a resolution of 0.25 hole diameters or better. The same wind-tunnel setup was simulated using the OVERFLOW Navier-Stokes equation solver. The information obtained was used primarily in qualitative comparisons of flow patterns. Overall good agreement was found in the definition of the expansion fan and barrier shock pattern produced by flow entering the normal holes, as well as three-dimensional flow patterns. Both studies agreed well in terms of measured mass flow rates, to within 1% of the boundary-layer mass flow. The presence of the barrier shock standing off the downstream edge of the bleed holes corresponded with a jet of upward flow, which may provide a mechanism for the generation of streamwise vortices.

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Validation of numerical simulations for investigating flow control in hypersonic inlets

Park

Nam

Kim

et al. 2023

Aerospace Science and Technology

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Modeling and Simulation of Bleed Holes in the Presence of Shock Wave/Boundary Layer Interaction

Cited by 7 publications

References 7 publications

Comparison of Experimental and Computational Flow Structure Investigations of a Normal-Hole Bled Supersonic Boundary Layer

Comparison of Experimental and Computational Flow Structure Investigations of a Normal-Hole Bled Supersonic Boundary Layer

Experimental and Computational Investigations of a Normal-Hole-Bled Supersonic Boundary Layer

Validation of numerical simulations for investigating flow control in hypersonic inlets

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