Combined Magnetohydrodynamic and Geometric Optimization of a Hypersonic Inlet

Abstract

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.

CFD Simulation Strategy for Hypersonic Aerodynamic Heating around a Blunt Biconic

“…Based on the analysis of the heat flux numerical results at stagnation point with different meshing grids, the wall cell Reynolds number is suggested to be 1 (2) The dependence between the turbulence model and the discretization scheme cannot be ignored. It seems hard to analyze these two factors independently.…”

“…Although it is based on the accurate and robust near-wall formulation of the Wilcox k − ω model, the additional near-wall functions are still somewhat unwieldy, so the performance of the SA model is still better than that of the SST model. (2) Near the outer edge of the boundary layer and in shear layers, the SST model blends into a transformed version of the k − ε formulation, thus providing the same good predictions for temperature and pressure in the flow fields as the SA model (see in Figures 4-6). (3) The main additional complexity in the SST model formulation compared to standard models lies in the necessity to compute the distance from the wall, which results in a longer calculation time than the SA model.…”

“…The wall cell Reynolds number [23] refers to the local Reynolds number based on the velocity in the calculation cell and the length scale of the cell, as shown in Equation (2). In which, R e denotes the Reynolds number in Table 1.…”

“…The axisymmetric shape is widely used in hypersonic missiles, such as the Kinzhal missile and the AHW [1] program. Hypersonic vehicles achieve high speeds (Mach 5-20) via rocket propulsion or scramjet engines [2], high lift-drag design [3,4], and the advantage of near-space. On the one hand, high-speed flight makes it difficult to detect and track the hypersonic vehicle.…”

Experimental Investigation of Brazilian 14-X B Hypersonic Scramjet Aerospace Vehicle

“…of full external compression and excessive viscous effects during full internal compression. The optimal cowl inlet configuration is the well-known "shock-on-lip" condition shown in Figure 5 [17].…”