Bleed-boundary conditions for numerically simulated mixed-compression supersonic inlet flow

Chyu, W. J.; Howe, Gregory; Shih, T. I.-P.

doi:10.2514/3.23561

Cited by 22 publications

(5 citation statements)

References 7 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The bleed boundary condition was rstorder extrapolation for all of the variables, except for the normal velocity that was determined based on uniform bleed mass ow rate. 10 This boundary condition, similar to the BC type 5 suggested by Chyu et al, 19 was proven to be a reasonable approximation to the slot bleed used in the experiment. 10…”

Section: B Boundary Conditionsmentioning

confidence: 82%

Investigations of High-Speed Civil Transport Inlet Unstart at Angle of Attack

Zha

Knight

Smith

1998

Journal of Aircraft

View full text Add to dashboard Cite

The unstart transient of a high-speed civil transport mixed compression axisymmetric inlet at Mach 2 and 2-deg angle of attack was investigated numerically by using a three-dimensional time-accurate Navier-Stokes solver. The Baldwin -Lomax algebraic turbulence model and an extrapolation uniform mass bleed boundary condition for the slot bleed were employed. It is observed that, when an angle of attack is imposed, the ow on the leeward side has a stronger compression than that at zero angle of attack. The strong compression reduces the Mach number upstream of the terminal shock and therefore makes the shock move upstream rst on the leeward side. The initial shock motion starts with the bifurcation of the terminal shock. The lower part of the split shock is stable because of the centerbody bleed, whereas the top part of the shock continues to travel upstream. When the terminal shock on the leeward side passes the bleed region, a separation is induced by the shock /boundary-layer interaction on the shoulder of the inlet centerbody, and the entire inlet is brought to unstart. The overall computed ow eld phenomena agree qualitatively with the experimental observations. Nomenclature M`= freestream Mach number P t`= freestream total pressure R c = radius at cowl leading edge T t`= freestream total temperature t c = characteristic time a = angle of attack Dr = grid point interval in radial direction 1 Dr 1 = (Dr 1 u t )/n D x = grid point interval in axial direction d = boundary-layer thickness on centerbody

show abstract

Section: B Boundary Conditionsmentioning

confidence: 82%

Investigations of High-Speed Civil Transport Inlet Unstart at Angle of Attack

Zha

Knight

Smith

1998

Journal of Aircraft

View full text Add to dashboard Cite

show abstract

“…Our numerical tests showed that this bleed boundary condition was robust. The current bleed boundary condition is similar to the BC type 5 suggested by Chyu et al [22]. The dierence is that we do not not use the momentum equation to solve the pressure.…”

Section: Boundary Conditionsmentioning

confidence: 96%

“…We found that the momentum equation was not easily simplied and introduced numerical instability. In addition, we impose the rst order derivative of the tangential velocity to be zero instead of the second order derivative to be zero as in [22]. The present bleed boundary condition was incorporated into the GASP code by the authors.…”

Section: Boundary Conditionsmentioning

confidence: 99%

Numerical simulation of HSCT inlet operability with angle of attack

Zha

Knight

Smith

et al. 1997

33rd Joint Propulsion Conference and Exhibit

View full text Add to dashboard Cite

A High Speed Civil Transport (HSCT) inlet at Mach 2 and angle of attack is simulated by using a 3D Navier-Stokes solver with the Baldwin-Lomax algebraic turbulence model. An extrapolation uniform mass bleed boundary condition for the slot bleed is successfully employed. For zero angle of attack and critical operation, the pressure distribution agrees well with the experiment. The location and intensity of the terminal shock, total pressure recovery are accurately computed. The angle of attack to cause the inlet unstart is accurately predicted. The mesh renement results are presented.

show abstract

“…Since it is not feasible to resolve the flow through each bleed hole in practical configurations that may involve hundreds to thousands of holes connected to different plenums, it is important to develop "bleed" boundary conditions (BCs) over surfaces with bleed holes that model the key flow physics created by the bleed process [24]. Chyu, et al [25] developed and evaluated several bleed BCs for a mixed-compression inlet in which the bleed region was modeled as a porous surface. Reasonably good agreement with the experimental data of Smeltzer & Sorensen [26] was found when the bleed through the holes was choked.…”

Section: Overviewmentioning

confidence: 99%

Control of Shock-Wave/Bound-Layer Interactions by Bleed

Shih

2008

International Journal of Fluid Machinery and Systems

View full text Add to dashboard Cite

Bleeding away a part of the boundary layer next to the wall is an effective method for controlling boundary-layer distortions from incident shock waves or curvature in geometry. When the boundary-layer flow is supersonic, the physics of bleeding with and without an incident shock wave is more complicated than just the removal of lower momentum fluid next to the wall. This paper reviews CFD studies of shock-wave/boundary-layer interactions on a flat plate with bleed into a plenum through a single hole, three holes in tandem, and four rows of staggered holes in which the simulation resolves not just the flow above the plate, but also the flow through each bleed hole and the plenum. The focus is on understanding the nature of the bleed process.

show abstract

Bleed-boundary conditions for numerically simulated mixed-compression supersonic inlet flow

Cited by 22 publications

References 7 publications

Investigations of High-Speed Civil Transport Inlet Unstart at Angle of Attack

Investigations of High-Speed Civil Transport Inlet Unstart at Angle of Attack

Numerical simulation of HSCT inlet operability with angle of attack

Control of Shock-Wave/Bound-Layer Interactions by Bleed

Contact Info

Product

Resources

About