Numerical and experimental investigation of the hypersonic flow structure in a complex flat duct

Authors: Kotov M.A., Kryukov I.A., Ruleva L.B., Solodovnikov S.I., Surzhikov S.T. Published: 09.02.2015
Published in issue: #1(100)/2015  

DOI: 10.18698/0236-3941-2015-1-4-21

Category: Aviation and Rocket-Space Engineering | Chapter: Aerodynamics and Heat Transfer Processes in Aircrafts  
Keywords: shock tube, experimental investigation, hypersonic flows, shockwave mathematical modelling, gas dynamics equations, compressible Navier-Stokes equations, finite volume approach

Experimental and numerical investigation was performed to determine the hypersonic flow structure in a complex flat duct simulating the air intake and flow passage in a hypersonic ramjet. The testing setup is described in detail. Mach 7 and Mach 4.5 air flows are studied by means of high-speed digital video cameras in the flat ducts formed by sharp and blunt-nose wedges. The duct internal surface was either smooth or had trapezoid cavities similar to flameholders in a hypersonic ramjet engine combustion chamber. The numerical simulation was conducted with the software (computer code) integrating the Navier-Stokes equation system. The comparison of testing and computational data proves that numerical simulation can provide accurate description of the experimental flow structure. The numerical and experimental results clearly present hypersonic flow field structure in complex configuration ducts. Simultaneous computational and experimental investigation enhances the reliability of the aerodynamic data obtained.


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