Numerical Simulation of Disturbance Evolution in the Supersonic Boundary Layer over an Expansion Corner
نویسندگان
چکیده
Abstract— The linear and nonlinear stages of disturbance development in the supersonic boundary layer over a 10° expansion corner is investigated numerically within framework Navier—Stokes equations for Mach number 3. effect sudden flow on evolution analyzed. stabilization observable aerodynamic experiment also discussed.
منابع مشابه
Numerical Simulation of Shock-Wave/Boundary/Layer Interactions in a Hypersonic Compression Corner Flow
Numerical results are presented for the shock-boundary layer interactions in a hypersonic flow over a sharp leading edge compression corner. In this study, a second- order Godunov type scheme based on solving a Generalized Riemann Problem (GRP) at each cell interface is used to solve thin shear layer approximation of laminar Navier-Stokes (N-S) equations. The calculated flow-field shows general...
متن کاملNumerical Simulation of MHD Boundary Layer Stagnation Flow of Nanofluid over a Stretching Sheet with Slip and Convective Boundary Conditions
An investigation is carried out on MHD stagnation point flow of water-based nanofluids in which the heat and mass transfer includes the effects of slip and convective boundary conditions. Employing the similarity variables, the governing partial differential equations including continuity, momentum, energy, and concentration have been reduced to ordinary ones and solved by using...
متن کاملLarge-eddy simulation of turbulent flow over an array of wall-mounted cubes submerged in an emulated atmospheric boundary-layer
Turbulent flow over an array of wall-mounted cubic obstacles has been numerically investigated using large-eddy simulation. The simulations have been performed using high-performance computations with local cluster systems. The array of cubes are fully submerged in a simulated deep rough-wall atmospheric boundary-layer with high turbulence intensity characteristics of environmental turbulent fl...
متن کاملNumerical Simulation of Laminar Film Cooling in a Supersonic Boundary Layer using Modeled and Simulated Blowing
Direct numerical simulations are used to investigate the method of film cooling in a laminar flat-plate Mach-2.67 boundary layer. Air is employed as mean-flow and coolant gas and is injected into an adiabatic or isothermal boundary layer through one or two rows of staggered, discrete holes. Previous simulations were performed using a modeled blowing approach, where the mass flux and temperature...
متن کاملDirect Numerical Simulation of Supersonic Turbulent Boundary Layer with Spanwise Wall Oscillation
Weidan Ni 1,†, Lipeng Lu 1,†, Catherine Le Ribault 2,† and Jian Fang 1,3,*,† 1 National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics, School of Energy and Power Engineering, Beihang University, 37 Xueyuan Road, Haidian District, Beijing 100191, China; [email protected] (W.N.); [email protected] (L.L.) 2 Laboratoire de Mécanique Des Fluides (LMFA), Ecole Centrale...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: Fluid Dynamics
سال: 2021
ISSN: ['1573-8507', '0015-4628']
DOI: https://doi.org/10.1134/s0015462821050025