Performance enhancement of three-dimensional hypersonic inlet with sidewall compression

Liang, Jian; Fan, X-Q; Wang, Y; Liu, W-D

doi:10.1243/09544100jaero334

Cited by 11 publications

(7 citation statements)

References 22 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…There have been many papers devoted to the investigation on the inlet design and inlet unstart. Wang (4) , Mahapatra (5) and Liang (6) studied the numerical simulation of hypersonic inlet, and Haberle (7,8) investigated scramjet inlet at Mach number 7. Chang (9,10) investigated hypersonic inlet with pulse periodic energy addition.…”

Section: Effect Of Boundary Layer Bleeding On Unstart Oscillatory Flomentioning

confidence: 99%

Effects of boundary-layer bleeding on unstart oscillatory flow of hypersonic inlets

Fan¹,

Chang²,

Bao³

et al. 2010

Aeronaut. j.

View full text Add to dashboard Cite

The unsteady flowfield of a series of mixed-compression hypersonic inlets with different bleeding rates were numerically simulated. Firstly unstart oscillatory flow of hypersonic inlets caused by downstream massflow choking was discussed. Then the effects of boundary layer bleeding on the averaged performance parameter of hypersonic inlets, and on the dominant amplitude and frequency of unstart oscillatory flow of hypersonic inlets were presented. The reasons why the boundary-layer bleeding can suppress unstart oscillatory flow of hypersonic inlets were analysed. In conclusion, the averaged performance parameter of hypersonic inlets during a big buzz is improved greatly, and the dominant frequency of unstart oscillatory flow of hypersonic inlets is reduced in contrast with no bleeding, and all these are benefit to the design and operation of hypersonic inlets.

show abstract

Section: Effect Of Boundary Layer Bleeding On Unstart Oscillatory Flomentioning

confidence: 99%

Effects of boundary-layer bleeding on unstart oscillatory flow of hypersonic inlets

Fan¹,

Chang²,

Bao³

et al. 2010

Aeronaut. j.

View full text Add to dashboard Cite

show abstract

“…Much CFD work has been done on hypersonic inlet [32][33][34][35] and HIT's CFD computation was performed using the finite-volume technique with upwind discretization to solve the two-dimensional compressible Reynolds-averaged Navier-Stokes equations and space discretization was performed by a cell-centreed formulation. A multi-grid method, implicit residuals smoothing, and local time stepping were applied to enhance convergence, and a value of y+ below 5 was realized for the main portion of the wall flow region to ensure the accuracy of the turbulence flow solution.…”

Section: Propulsionmentioning

confidence: 99%

Modelling for couplings of an airframe—propulsion integrated hypersonic vehicle with engine safety boundaries

Yao

Bao

Chang

et al. 2009

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

A model for coupled dynamics of an airframe-propulsion integrated hypersonic airbreathing flight vehicle with various engine safety boundaries, called HIT-HAV (Harbin Institute of Technology), was developed to analyse the couplings among flight dynamics, aerodynamics, propulsion, and control. These engine safety boundaries included inlet unstart boundary, burner wall temperature limitation, burner lean fuel combustion boundary, rich fuel combustion boundary, and so on. All these engine safety boundaries were considered in modelling the HIT-HAV. The validity and practicability of the model were verified by comparing with a full-scale generic hypersonic vehicle. By simulating the HIT-HAV model, the conclusion was drawn that due to the couplings among flight dynamics, aerodynamics, propulsion, and control, the airframepropulsion integrated hypersonic air-breathing flight vehicle may operate, beside the normal operation mode, near some safety boundaries and may even exceed them, which may cause a failure flight. A hypersonic air-breathing flight vehicle's un-safety operation mode could be avoided by limiting the fuel supply, which has been verified in simulations. This paper indicates that for an airframe-propulsion integrated hypersonic air-breathing flight vehicle with various engine safety boundaries, as there were various relevant operation modes requested by various engine safety boundaries, an independent flight control and propulsion control in the traditional sense would fail to satisfy the hypersonic air-breathing flight and hence a multi-mode control design should be the focus of future research.

show abstract

“…Hypersonic inlets have also been considered in the past few years. [10][11][12] Nair et al 10 used Reynolds-averaged Navier-Stokes to compute the flow through a hypersonic inlet to conduct a detailed aerodynamic analysis. The effects of the position of the sidewall compression and the cowl deflection angle on the inlet performance were investigated to improve the mass flow rate at design point.…”

Section: Introductionmentioning

confidence: 99%

“…The results showed that the sidewall compression affects the mass flow, whereas the cowl deflection angle manipulates the inlet starting characteristics. 11 New methods such as energy addition were used to improve the performance parameters. Chang et al 12 numerically studied the effects of pulse periodic energy addition to hypersonic inlets and its main factors such as pulsed frequency on the performance parameters.…”

Section: Introductionmentioning

confidence: 99%

Performance study of an inlet in supersonic flow

Soltani

Farahani

2012

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

The performance characteristics of an axisymmetric inlet at its design and off-design operational conditions are experimentally investigated. The model is tested for wide ranges of free stream Mach numbers, M∞ = 1.5–2.5, and mass flow rates. For each test, the pressure recovery, the mass flow passing through the inlet and the pressure distribution over the spike and the cowl are measured. In addition, the shock wave formed in front of the inlet is visualized. The characteristic curve of the inlet is then obtained for each free stream Mach number. As the Mach number is increased, the pressure recovery is reduced, but the maximum value of the mass flow rate grows up. Variations of the mass flow affect the surface pressure over both the front portion of the cowl and the entire surface of the spike. Further, it has changed both pressure and Mach number at the end of the diffuser, which would consequently affect the performance of the propulsion system. In addition, contrary to the internal boundary layer, the external one far from the cowl lip has been found to be almost independent of the inlet mass flow rate for a constant free stream Mach number.

show abstract

Performance enhancement of three-dimensional hypersonic inlet with sidewall compression

Cited by 11 publications

References 22 publications

Effects of boundary-layer bleeding on unstart oscillatory flow of hypersonic inlets

Effects of boundary-layer bleeding on unstart oscillatory flow of hypersonic inlets

Modelling for couplings of an airframe—propulsion integrated hypersonic vehicle with engine safety boundaries

Performance study of an inlet in supersonic flow

Contact Info

Product

Resources

About