Numerical study of flow X-43 hypersonic aircraft using adaptive grids

Numerical Study of Non - Equilibrium Air Dissociation For Calculation of Electron Density in Hypersonic Flow

Numerical Study of Hypersonic Turbulent Flow about Segmented Projectiles

The flow structure about a segmented projectile in hypersonic turbulent flow has been studied. The Reynoldsaveraged Navier-Stokes equations were solved numerically by application of the implicit monotonized scheme of second-order accuracy, the modified Newton's method, and the Christoffel-Schwarz grid-transformation technique. A strong interference effect has been found. The effect can be chara...

Numerical Simulation of Weakly Ionized Hypersonic Flow for Reentry Configurations

Numerical simulations of axisymmetric flows over reentry configurations at hypersonic conditions using a Navier-Stokes solver are presented. The Navier-Stokes equations are modified using Park’s two-temperature model to account for thermochemical nonequilibrium and weak ionization effects. The finite-volume method is used to solve the set of differential equations. The code has the capability t...

Numerical Investigations of Effusion Cooling in Hypersonic Boundary-Layer Flow

Direct numerical simulations (DNS) are carried out to investigate the effect of effu-sion cooling by blowing through spanwise slits and discrete holes in a laminar flat-plate boundary layer at various Mach numbers. The comparison with experimental data for a Mach-2.67 boundary layer with a cool wall and a spanwise slit shows good agreement. For an adiabatic Mach-6 boundary layer, the focus of t...

Adaptive Control Using Support Vector Regression for Hypersonic Aircraft Control System

This paper presents support vector regression (SVR)-based adaptive controller for the longitudinal dynamics of a generic hypersonic aircraft. SVR has been proven to generate global solutions contrary to neural networks, because SVR basically solves quadratic programming (QP) problems. With this advantage, the nominal dynamics of the input-output feedback-linearized hypersonic airplane is traine...