Linearized Navier-Stokes Calculations of the Spatial Stability of a Hypersonic Boundary Layer on a 5°Sharp Cone with High Temperature Effects

2014 ◽  
Author(s):  
Leonardo Salemi ◽  
Andreas Gross ◽  
Hermann F. Fasel ◽  
Stefan H. Wernz ◽  
Edward Marquart
Keyword(s):  
Boundary Layer ◽  
High Temperature ◽  
Temperature Effects ◽  
Navier Stokes ◽  
Hypersonic Boundary Layer ◽  
Spatial Stability ◽  
Sharp Cone

Statistical Analysis of Nonlinear Processes on a Porous Surface in a Hypersonic Boundary Layer

2009 ◽  
Vol 4 (3) ◽  
pp. 43-49
Author(s):  
Dmitriy Buntin ◽  
Anatoliy Maslov ◽  
Timur Chimytov ◽  
Aleksandr Shiplyuk
Keyword(s):  
Boundary Layer ◽  
Statistical Analysis ◽  
Porous Surface ◽  
Transition To Turbulence ◽  
Hypersonic Boundary Layer ◽  
Hot Wire ◽  
Turbulent Transition ◽  
Hypersonic Wind Tunnel ◽  
Sharp Cone ◽  
Skewness And Kurtosis

Experimental investigation of nonlinear stage of the transition to turbulence in a hypersonic boundary layer is presented. The experiments were carried out in a hypersonic wind tunnel T-326 at the Institute of theoretical and applied mechanics SB RAS. The model was a sharp cone with porous surface. Using the statistical analysis of the signals obtained by means of hot-wire it was shown that skewness and kurtosis distribution in a boundary layer on both solid and porous surface are in a qualitative agreement. At the same time the growing of skewness and kurtosis on a porous surface was shown. Analysis of mean voltage and rms voltage pulsation profiles of the hot-wire sensors showed that there is a delay of the laminar-turbulent transition on a porous surface.

Leading-edge receptivity to free-stream disturbance waves for hypersonic flow over a parabola

2001 ◽  
Vol 441 ◽  
pp. 315-367 ◽  
Author(s):  
XIAOLIN ZHONG
Keyword(s):  
Boundary Layer ◽  
Hypersonic Flow ◽  
Boundary Layers ◽  
Free Stream ◽  
Stokes Equations ◽  
Leading Edge ◽  
Bow Shock ◽  
Navier Stokes ◽  
Hypersonic Boundary Layer ◽  
Disturbance Waves

The receptivity of hypersonic boundary layers to free-stream disturbances, which is the process of environmental disturbances initially entering the boundary layers and generating disturbance waves, is altered considerably by the presence of bow shocks in hypersonic flow fields. This paper presents a numerical simulation study of the generation of boundary layer disturbance waves due to free-stream waves, for a two-dimensional Mach 15 viscous flow over a parabola. Both steady and unsteady flow solutions of the receptivity problem are obtained by computing the full Navier–Stokes equations using a high-order-accurate shock-fitting finite difference scheme. The effects of bow-shock/free-stream-sound interactions on the receptivity process are accurately taken into account by treating the shock as a discontinuity surface, governed by the Rankine-Hugoniot relations. The results show that the disturbance waves generated and developed in the hypersonic boundary layer contain both first-, second-, and third-mode waves. A parametric study is carried out on the receptivity characteristics for different free-stream waves, frequencies, nose bluntness characterized by Strouhal numbers, Reynolds numbers, Mach numbers, and wall cooling. In this paper, the hypersonic boundary-layer receptivity is characterized by a receptivity parameter defined as the ratio of the maximum induced wave amplitude in the first-mode-dominated region to the amplitude of the free-stream forcing wave. It is found that the receptivity parameter decreases when the forcing frequency or nose bluntness increase. The results also show that the generation of boundary layer waves is mainly due to the interaction of the boundary layer with the acoustic wave field behind the bow shock, rather than interactions with the entropy and vorticity wave fields.

Evolution of nonlinear processes in a hypersonic boundary layer on a sharp cone

2008 ◽  
Vol 611 ◽  
pp. 427-442 ◽  
Author(s):  
D. BOUNTIN ◽  
A. SHIPLYUK ◽  
A. MASLOV
Keyword(s):  
Boundary Layer ◽  
Mach Number ◽  
Basic Mechanism ◽  
Hypersonic Boundary Layer ◽  
Nonlinear Interactions ◽  
Nonlinear Processes ◽  
Voltage Fluctuation ◽  
Second Mode ◽  
Sharp Cone ◽  
Second Mode Of Disturbances

Nonlinear processes in a hypersonic boundary layer on a sharp cone are considered using the bicoherence method. The experiments are performed for a Mach number M∞ = 5.95 with introduction of artificial wave packets at the frequency of the second mode. It is shown that the basic mechanism of nonlinear interaction at the location of the maximum r.m.s. voltage fluctuation is the subharmonic resonance; all nonlinear interactions in the maximum r.m.s. voltage fluctuation layer are related to the second mode of disturbances; nonlinear processes above and below that layer are much more intense than those in it. The effect of artificial disturbances on nonlinear interactions in the boundary layer is shown to be insignificant.

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