A calculation approach for shock layer radiation and transmittance towards hypersonic infrared homing vehicle

2021 ◽  
Author(s):  
Mingqi Pang ◽  
ZeLin Shi ◽  
Daijun Zhang ◽  
Haizheng Liu
Keyword(s):  
Shock Layer

MHD Control of the Hypersonic Flow in the Shock Layer Around a Body

2008 ◽  
Author(s):  
Andrea Cristofolini ◽  
Carlo Borghi ◽  
Gabriele Neretti ◽  
Andrea Passaro ◽  
Leonardo Biagioni
Keyword(s):  
Hypersonic Flow ◽  
Shock Layer

Trajectory and Thermal Analysis for Disk-shaped Dust Particles through a Shock Layer

2014 ◽  
Author(s):  
Yoshihiro Toki ◽  
Yousuke Ogino ◽  
Naofumi Ohnishi ◽  
Keisuke Sawada
Keyword(s):  
Thermal Analysis ◽  
Shock Layer ◽  
Dust Particles

The Influence of Particulates on Thruster Plume / Shock Layer Interaction at High Altitudes

2005 ◽  
Author(s):  
Sergey F. Gimelshein ◽  
Alina A. Alexeenko ◽  
Dean C. Wadsworth ◽  
Natalia E. Gimelshein
Keyword(s):  
Shock Layer ◽  
High Altitudes ◽  
Layer Interaction

A numerical study on the single pulsed energy addition based unsteady wave drag reduction at varied hypersonic flow regimes

2020 ◽  
pp. 095441002097313
Author(s):  
Dathi SNV Rajasekhar Rao ◽  
Bibin John
Keyword(s):  
Steady State ◽  
Mach Number ◽  
Drag Reduction ◽  
Shock Layer ◽  
Blunt Body ◽  
Wave Drag ◽  
Flow Features ◽  
Energy Pulse ◽  
Energy Addition ◽  
Wave Drag Reduction

In this study, unsteady wave drag reduction in hypersonic flowfield using pulsed energy addition is numerically investigated. A single energy pulse is considered to analyze the time-averaged drag reduction/pulse. The blast wave creation, translation and its interaction with shock layer are studied. As the wave drag depends only on the inviscid aspects of the flowfield, Euler part of a well-established compressible flow Navier-Stokes solver USHAS (Unstructured Solver for Hypersonic Aerothermodynamics) is employed for the present study. To explore the feasibility of pulsed energy addition in reducing the wave drag at different flight conditions, flight Mach numbers of 5.75, 6.9 and 8.0 are chosen for the study. An [Formula: see text] apex angle blunt cone model is considered to be placed in such hypersonic streams, and steady-state drag and unsteady drag reductions are computed. The simulation results indicate that drag of the blunt-body can be reduced below the steady-state drag for a significant period of energy bubble-shock layer interaction, and the corresponding propulsive energy savings can be up to 9%. For energy pulse of magnitude 100mJ deposited to a spherical region of 2 mm radius, located 50 mm upstream of the blunt-body offered a maximum percentage of wave drag reduction in the case of Mach 8.0 flowfield. Two different flow features are found to be responsible for the drag reduction, one is the low-density core of the blast wave and the second one is the baroclinic vortex created due to the plasma energy bubble-shock layer interaction. For the same freestream stagnation conditions, these two flow features are noted to be very predominant in the case of high Mach number flow in comparison to Mach 5.75 and 6.9 cases. However, the ratio of energy saved to the energy consumed is noted as a maximum for the lower Mach number case.

Higher-order viscous shock-layer solutions for high altitude flows

1993 ◽  
Author(s):  
ROOP GUPTA ◽  
SUDHEER NAYANI ◽  
KAM-PUI LEE ◽  
ERNEST ZOBY
Keyword(s):  
High Altitude ◽  
Shock Layer ◽  
Higher Order ◽  
Viscous Shock Layer

Nonequilibrium shock layer temperature profiles from arc jet radiation measurements

1989 ◽  
Author(s):  
HARVEL BLACKWELL ◽  
ERIC YUEN ◽  
CARL SCOTT ◽  
SIVARAM AREPALLI
Keyword(s):  
Shock Layer ◽  
Temperature Profiles ◽  
Radiation Measurements
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