Numerical simulation of HSCT inlet operability with angle of attack

Zha, Gecheng; Knight, Doyle; Smith, Donald; Haas, Martín

doi:10.2514/6.1997-2761

Cited by 8 publications

(1 citation statement)

References 15 publications

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“…10 We continue to use this model here for its ef ciency and fairly good accuracy performance. Because the Roe scheme failed in three-dimensional ow as a result of an anomalous solution, 18 the Van Leer upwind scheme was used in our computation to evaluate the inviscid uxes. The other important merit of the Van Leer scheme was that the allowable CourantFriedrichs-Lewy (CFL) was about ve times higher than that of the Roe scheme.…”

Section: A Flow Solvermentioning

confidence: 99%

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

Zha

Knight

Smith

1998

Journal of Aircraft

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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

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Section: A Flow Solvermentioning

confidence: 99%

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

Zha

Knight

Smith

1998

Journal of Aircraft

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Shock wave bifurcation in convergent–divergent channels of rectangular cross section

Kuzmin

2016

Shock Waves

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Transonic flow instability in the entrance region of a channel with breaks of walls

Kuzmin

2017

Arch Appl Mech

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We study numerically turbulent flow of the air in a channel with breaks of walls. The flow is supersonic downstream of the break section and in the free stream. Instability of shock waves formed in the channel and in front of the entrance is examined. Solutions of the Reynolds-averaged Navier-Stokes equations are obtained with a finite-volume solver of second-order accuracy. The solutions demonstrate an expulsion/swallowing of the shock waves with variation of the free-stream Mach number. Effects of the upper wall slopes on the shock wave positions and flow bifurcation are examined.

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Numerical simulation of HSCT inlet operability with angle of attack

Cited by 8 publications

References 15 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

Shock wave bifurcation in convergent–divergent channels of rectangular cross section

Transonic flow instability in the entrance region of a channel with breaks of walls

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