Visualization of Shock Wave Phenomenon around a Sharp Cone Model at Hypersonic Mach Number in a Shock Tunnel using High Speed Schlieren Facility
Publish place: Journal of Applied Fluid Mechanics، Vol: 12، Issue: 2
Publish Year: 1398
نوع سند: مقاله ژورنالی
زبان: English
View: 164
This Paper With 8 Page And PDF Format Ready To Download
- Certificate
- من نویسنده این مقاله هستم
استخراج به نرم افزارهای پژوهشی:
شناسه ملی سند علمی:
JR_JAFM-12-2_014
تاریخ نمایه سازی: 15 دی 1400
Abstract:
The flow field around a Sharp cone model configuration has been investigated by means of Schlieren facility in hypersonic shock tunnel. The time dependent evolution of flow around a cone of angle ۱۱.۳۸° with base radius of ۱۵۰mm has been visualized for a flow Mach number M = ۶.۵. Experiments have been carried out with Helium as driver gas and air as test gas to visualize the hypersonic flow field. The flow establishment, steady state, and termination process of the hypersonic flow have been visualized for two different angles of attack, namely ۰°&۵°. Experimentally measured shock angle compares well with the theoretical and the computational study. The measured shock layer thickness compares well with the numerical simulation for both angles of attack.
Keywords:
Sharp Cone model , High speed Schlieren facility , Hypersonic shock , Tunnel , Shock layer thickness
Authors
M. Saiprakash
Department of Aerospace Engineering MIT Campus, Anna University, Chennai-۶۰۰۰۴۴,India
C. SenthilKumar
Department of Aerospace Engineering MIT Campus, Anna University, Chennai-۶۰۰۰۴۴,India
G. K. Sunil
Directorate of Aerodynamics, Defence Research & Development Laboratory, Hyderabad -۵۰۰۰۵۸, India
S. P. Rampratap
Directorate of Aerodynamics, Defence Research & Development Laboratory, Hyderabad -۵۰۰۰۵۸, India
V. Shanmugam
Directorate of Aerodynamics, Defence Research & Development Laboratory, Hyderabad -۵۰۰۰۵۸, India
G. Balu
Directorate of Aerodynamics, Defence Research & Development Laboratory, Hyderabad -۵۰۰۰۵۸, India