Investigation of REST-class Hypersonic Inlet Designs

An Innovative Integration Concept for Forebody and Two-Dimensional Hypersonic Inlet with Controllable Wall Pressure Distribution

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference ◽

10.2514/6.2015-3592 ◽

2015 ◽

Author(s):

Yiqing Li ◽

Weiqiang Han ◽

Jian Teng ◽

Yancheng You

Keyword(s):

Pressure Distribution ◽

Wall Pressure ◽

Two Dimensional ◽

Hypersonic Inlet ◽

Integration Concept

Download Full-text

Streamline Tracing Technique Based Design of Elliptical-to-Rectangular Transitioning Hypersonic Inlet

10.2514/6.2013-2665 ◽

2013 ◽

Cited By ~ 1

Author(s):

Mohd Rizal Rosli ◽

Masahiro Takahashi ◽

Tetsuya Sato ◽

Takayuki Kojima ◽

Hideyuki Taguchi ◽

...

Keyword(s):

Hypersonic Inlet ◽

Streamline Tracing

Download Full-text

Combined Magnetohydrodynamic and Geometric Optimization of a Hypersonic Inlet

International Journal of Aerospace Engineering ◽

10.1155/2009/793647 ◽

2009 ◽

Vol 2009 ◽

pp. 1-12 ◽

Cited By ~ 2

Author(s):

Kamesh Subbarao ◽

Jennifer D. Goss

Keyword(s):

Magnetic Field ◽

Numerical Optimization ◽

Splitting Method ◽

Optimization Procedure ◽

Geometric Optimization ◽

Control Parameters ◽

Flow Solution ◽

Hypersonic Inlet ◽

Mass Capture ◽

The Magnetic Field

This paper considers the numerical optimization of a double ramp scramjet inlet using magnetohydrodynamic (MHD) effects together with inlet ramp angle changes. The parameter being optimized is the mass capture at the throat of the inlet, such that spillage effects for less than design Mach numbers are reduced. The control parameters for the optimization include the MHD effects in conjunction with ramp angle changes. To enhance the MHD effects different ionization scenarios depending upon the alignment of the magnetic field are considered. The flow solution is based on the Advection Upstream Splitting Method (AUSM) that accounts for the MHD source terms as well. A numerical Broyden-Flecher-Goldfarb-Shanno- (BFGS-) based procedure is utilized to optimize the inlet mass capture. Numerical validation results compared to published results in the literature as well as the outcome of the optimization procedure are summarized to illustrate the efficacy of the approach.

Download Full-text

Numerical Study on Supersonic Combustor with an Allotype Cavity

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.694.187 ◽

2014 ◽

Vol 694 ◽

pp. 187-192

Author(s):

Jin Xiang Wu ◽

Jian Sun ◽

Xiang Gou ◽

Lian Sheng Liu

Keyword(s):

Alternative Model ◽

Numerical Study ◽

Reverse Flow ◽

Three Dimensional ◽

Flow Characteristics ◽

Experimental Result ◽

Navier Stokes ◽

Cold Flow ◽

Hypersonic Inlet ◽

Good Agreement

The three-dimensional coupled explicit Reynolds Averaged Navier–Stokes (RANS) equations and the two equation shear-stress transport k-w (SST k-w) model has been employed to numerically simulate the cold flow field in a special-shaped cavity-based supersonic combustor. In a cross-section shaped rectangular, hypersonic inlet with airflow at Mach 2.0 chamber, shock structures and flow characteristics of a herringbone-shaped boss and a herringbone-shaped cavity models were discussed, respectively. The results indicate: Firstly, according to the similarities of bevel-cutting shock characteristics between the boss case and the cavity case, the boss structure can serve as an ideal alternative model for shear-layer. Secondly, the eddies within cavity are composed of herringbone-spanwise vortexes, columnar vortices in the front and main-spanwise vortexes in the rear, featuring tilting, twisting and stretching. Thirdly, the simulated bottom-flow of cavity is in good agreement with experimental result, while the reverse flow-entrainment resulting from herringbone geometry and pressure gradient. However, the herringbone-shaped cavity has a better performance in fuel-mixing.

Download Full-text