Experimental investigation of the effect of a single bleed hole on a supersonic turbulent boundary-layer

Bodner, J.; Greber, Isaac; Davis, David O.; Hingst, W. R.

doi:10.2514/6.1996-2797

Cited by 22 publications

(11 citation statements)

References 5 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…As a result, the growing boundary layer along the wall of the inlet will experience adverse pressure gradients, possibly resulting in boundary-layer separation and even engine unstart. Bleed systems, which extract lowmomentum fluid from the boundary layer, have been demonstrated to reduce both boundary-layer thickness and the severity of separation [1]. However, bleed systems result in a loss of captured mass flow [2].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Microramp Flow Control of Normal Shock/Boundary-Layer Interactions

et al. 2010

View full text Add to dashboard Cite

Boundary-layer bleed has conventionally been used to control separation due to shock wave/boundary-layer interactions within supersonic engine inlets. However, bleed systems result in a loss of captured mass flow, incurring higher drag and, ultimately, lower propulsion system efficiency. Microramp sub-boundary-layer vortex generators arranged in a spanwise array have been proposed in the past as a form of flow-control methodology for shock wave/ boundary-layer interactions. Experiments have been conducted herein at Mach 1.4 to characterize flow details of such devices and obtain quantitative measurements of their ability to control the interaction of a normal shock with a turbulent boundary layer. The flowfield was analyzed using schlieren photography, surface oil flow visualization, pressure-sensitive paint, and particle image velocimetry. An array of three microramps, for which the height was scaled to 36% of the incoming boundary-layer thickness, was placed ahead of the normal shock interaction. It was demonstrated that the microramps did entrain higher-momentum fluid into the boundary layer, which improved boundary-layer health. Specifically, the incompressible displacement thickness, momentum thickness, and shape factor were decreased, and the skin friction coefficient was increased, for the shock wave/boundary-layer interaction with the microramp array relative to the no-array case.

show abstract

Section: Introductionmentioning

confidence: 99%

“…Three optimized geometries scaled by microramp height were derived, one for each criterion separately and one for which each criterion was equally weighted [10]. These optimized geometries have been the focus of several recent investigations [1,[12][13][14].…”

Section: Introductionmentioning

confidence: 99%

Microramp Flow Control of Normal Shock/Boundary-Layer Interactions

et al. 2010

View full text Add to dashboard Cite

show abstract

“…Information has primarily been restricted to flow coefficients and boundary layer velocity profiles both with and without an impinging oblique shock wave, [14][15][16][17] with only a few glimpses of the more complex 3D flow structure surrounding individual bleed holes, 18,19 which can be seen in figure 2, and their interaction within an array.…”

Section: B Previous Workmentioning

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

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.

show abstract

“…Bleed systems, which extract low-momentum fluid from the boundary layer, have been demonstrated to reduce both boundary layer thickness and the severity of separation. 1 However, bleed systems result in a loss of captured mass flow. 2 The reduction in captured mass flow results in the necessity for larger inlets, incurring higher drag and ultimately lower propulsion system efficiency.…”

Section: Introductionmentioning

confidence: 99%