Supersonic-inlet boundary-layer bleed flow
Gary J. Harloff,Gregory E. Smith +1 more
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In this paper, a new analytical bleed method is presented to compute sonic flow coefficients for holes and narrow slots and predictions are compared with published data to illustrate the accuracy of the model, which can be used by inlet designers and as a bleed boundary condition for computational fluid dynamic studies.Abstract:
Boundary-layer bleed in supersonic inlets is typically used to avoid separation from adverse shock-wave/boundary-layer interactions and subsequent total pressure losses in the subsonic diffuser and to improve normal shock stability. Methodologies used to determine bleed requirements are reviewed. Empirical sonic flow coefficients are currently used to determine the bleed hole pattern. These coefficients depend on local Mach number, pressure ratio, hole geometry, etc. A new analytical bleed method is presented to compute sonic flow coefficients for holes and narrow slots and predictions are compared with published data to illustrate the accuracy of the model. The model can be used by inlet designers and as a bleed boundary condition for computational fluid dynamic studies.read more
Citations
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Journal ArticleDOI
Pseudo-shock waves and their interactions in high-speed intakes
TL;DR: In this article, the main results on the shock train structure and its associated phenomena inside isolators, studied using the aforementioned tools are brought together, and several promising flow control techniques that have more recently been applied to manipulate the shock wave/boundary layer interaction are also examined.
Journal ArticleDOI
Internal Flowfield Investigation of a Hypersonic Inlet at Mach 6 with Bleed
Jürgen Häberle,Ali Gülhan +1 more
TL;DR: In this paper, an experimental study has been carried out on a fixed geometry scramjet inlet operating at Mach 6 using a hypersonic blowdown wind-tunnel facility.
Flowfield Measurements in a Slot-Bled Oblique Shock Wave and Turbulent Boundary-Layer Interaction
TL;DR: In this article, an experimental investigation was conducted to determine the flowfield inside a bleed slot used to control an oblique shock-wave and turbulent boundary-layer interaction, and the results showed that despite an initially two-dimensional interaction for the zero bleed-flow case, the slot does not remove mass uniformly in the spanwise direction.
Journal ArticleDOI
Experimental Investigation of a Two-Dimensional and a Three-Dimensional Scramjet Inlet at Mach 7
Jürgen Häberle,Ali Gülhan +1 more
TL;DR: In this paper, the viscous flow effects in a scramjet inlet with a fixed geometry operating at Mach 7.5-8.5 were investigated by means of static and pitot pressure plots.
Journal ArticleDOI
Effects of Boundary-Layer Bleed Parameters on Supersonic Intake Performance
TL;DR: In this article, the performance and the buzz onset of a supersonic mixed-compression axisymmetric intake were experimentally investigated and the results showed that applying the bleed at a position near the intake entrance and reducing the bleed entrance slant angle and width all improved the intake performance considerably.
References
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Journal ArticleDOI
Calculation of incompressible rough-wall boundary-layer flows
Tuncer Cebeci,K. C. Chang +1 more
TL;DR: The algebraic eddy viscosity model of Cebeci and Smith has been modified to account for wall roughness by incorporating a suggestion of Rotta as discussed by the authors, and the boundary-layer equations are solved, with this model, by the accurate and efficient Keller Box scheme for a wide variety of experimental configurations.
Journal ArticleDOI
Boundary conditions for unsteady supersonic inlet analyses
David W. Mayer,Gerald C. Paynter +1 more
TL;DR: In this paper, a new boundary condition was developed to improve the accuracy of unsteady supersonic inlet calculations, which relates changes in the bleed hole discharge coefficient to changes in local flow conditions; the local bleed flow rate can more than double as a shock moves forward over a bleed band.
Proceedings ArticleDOI
Flow Coefficient Behavior for Boundary Layer Bleed Holes and Slots
TL;DR: In this paper, an experimental investigation into the flow coefficient behavior for nine boundary layer bleed orifice configurations was conducted for the purposes of exploring boundary layer control through mass flow removal and does not address issues of stability bleed.
Journal ArticleDOI
Effect of Compressibility on the Discharge Coefficient of Orifices and Convergent Nozzles
TL;DR: It has been known for some time that when a gas flows through an orifice the coefficient of discharge increases as the ratio of the downstream pressure to the upstream pressure is reduced as mentioned in this paper.
Journal ArticleDOI
Bleed System Design Technology for Supersonic Inlets
Jan Syberg,Joseph L. Koncsek +1 more
TL;DR: In this article, a boundary-layer bleed system design procedure for supersonic inlets, with emphasis on the selection of bleed hole geometry, is described, and available experimental data, coupled with bleed drag calculations, show that holes with shallow inclination are superior to holes normal to the surface in terms of over-all inlet performance.
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