Hypersonic Shock Impingement Studies on a Flat Plate with Elevated Wall Temperatures

2021 ◽  
Author(s):  
◽  
Eric Won Keun Chang
Keyword(s):  
Flat Plate ◽  
Hypersonic Shock ◽  
Shock Impingement

Hypersonic shock impingement on a heated flat plate at Mach 7 flight enthalpy

2020 ◽  
Vol 908 ◽  
Author(s):  
Eric Won Keun Chang ◽  
Wilson Y. K. Chan ◽  
Timothy J. McIntyre ◽  
Ananthanarayanan Veeraragavan
Keyword(s):  
Flat Plate ◽  
Hypersonic Shock ◽  
Shock Impingement

Abstract

Shock-tunnel investigations on the evolution and morphology of shock-induced large separation bubbles

2016 ◽  
Vol 120 (1229) ◽  
pp. 1123-1152 ◽  
Author(s):  
R. Sriram ◽  
G. Jagadeesh
Keyword(s):  
Mach Number ◽  
Flat Plate ◽  
Surface Pressure ◽  
Separation Bubble ◽  
Leading Edge ◽  
Shock Tunnel ◽  
Total Enthalpy ◽  
Hypersonic Shock ◽  
Shock Impingement ◽  
Shock Tunnels

ABSTRACTShock-tunnel experiments are carried out to study the strong interaction between an impinging shock wave and boundary layer on a flat plate, accompanied bylargeseparation bubble with a length comparable to the distance of the location of shock impingement from the leading edge of the plate. For nominal freestream Mach numbers ranging from 6 to 8.5, moderate to high total enthalpies of 1.3MJ/kg to 6MJ/kg are simulated in the Indian Institute of Science's hypersonic shock tunnels HST-2 (a conventional Hypersonic Shock Tunnel) and Free Piston Shock Tunnel (FPST) with freestream Reynolds numbers ranging from 4 × 106/m to 0.3 × 106/m. The strong impinging shock is generated by a wedge (or shock generator) at an angle of 30.96° to the freestream. From the time-resolved Schlieren flow visualisations using a high-speed camera and surface pressure measurements on the flat plate using fast response sensors, a statistically steady flow field with a large separation bubble was established within the short test time of the shock tunnels (around 600µs in HST-2 and 300µs in FPST). The role of various parameters on the interaction – Mach number, location of shock impingement and flow total enthalpy – are investigated from the measured separation length and surface pressure distribution. For the nominal Mach number of 8.5, with shock impingement at 100mm from the leading edge, the separation length increased from 60mm to 70mm as the total enthalpy is increased from 1.6MJ/kg to 2.4MJ/kg; whereas it dropped drastically to 30-40mm at 6MJ/kg. This is due to the prominence of real gas effects at higher enthalpies.

Stability of the Hypersonic Shock Layer on a Flat Plate

2004 ◽  
Vol 39 (2) ◽  
pp. 181-188 ◽  
Author(s):  
A. A. Maslov ◽  
S. G. Mironov ◽  
T. V. Poplavskaya ◽  
B. V. Smorodskii
Keyword(s):  
Flat Plate ◽  
Shock Layer ◽  
Hypersonic Shock Layer ◽  
Hypersonic Shock

Experimental study of secondary instability in a hypersonic shock layer on a flat plate

2000 ◽  
Vol 412 ◽  
pp. 259-277 ◽  
Author(s):  
S. G. MIRONOV ◽  
A. A. MASLOV
Keyword(s):  
Flat Plate ◽  
Shock Layer ◽  
Streamwise Vortex ◽  
Finite Amplitude ◽  
Vortex Structures ◽  
Density Fluctuations ◽  
Secondary Instability ◽  
Complex Data ◽  
Hypersonic Shock Layer ◽  
Hypersonic Shock

The development of secondary instability on streamwise vortex structures generated in a hypersonic shock layer on a flat plate is experimentally studied for the flow with Mach number M∞ = 21 and unit Reynolds number Re1 = 6 × 105 m−1. The study is performed using the electron-beam method. The generation of weak unsteady vortices and steady streamwise vortex structures with finite-amplitude perturbations imposed onto them is studied in detail. Complex data on the characteristics of density fluctuations developed on quasi-steady and unsteady streamwise vortex structures are obtained. It is shown that the characteristics of the natural fluctuations of density developing in the shock layer on a flat plate are qualitatively similar to density fluctuations induced by weak unsteady vortex perturbations introduced into the shock layer. The possibility of existence of parametric resonance between the fundamental frequency and its harmonic and between harmonics for steady streamwise vortex structure is shown.

Study of the distributed and localized susceptibility of a hypersonic shock layer on a plate

2008 ◽  
Vol 3 (2) ◽  
pp. 21-27
Author(s):  
Tatyana V. Poplavskaya ◽  
Alexey N. Kudryavtsev ◽  
Ivan S. Tsyryulnikov ◽  
Sergey G. Mironov
Keyword(s):  
Flat Plate ◽  
Shock Layer ◽  
External Flow ◽  
Plate Model ◽  
Hypersonic Shock Layer ◽  
Hypersonic Shock

Investigations of a receptivity and disturbances evolution generated in a hypersonic shock layer on a flat plate under the action of disturbances of the external flow and disturbances, entered in a shock layer locally on the surface of the plate model is represented in work

Stability of a hypersonic shock layer on a flat plate

2004 ◽  
Vol 332 (11) ◽  
pp. 875-880 ◽  
Author(s):  
Anatoly A. Maslov ◽  
Tatiana V. Poplavskaya ◽  
Boris V. Smorodsky
Keyword(s):  
Flat Plate ◽  
Shock Layer ◽  
Hypersonic Shock Layer ◽  
Hypersonic Shock
Sign in / Sign up

Export Citation Format

Share Document