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AERODYNAMICS AND HEAT EXCHANGE

PROCESSES OF AIRCRAFT

NUMERICAL AND EXPERIMENTAL INVESTIGATION

OF THE HYPERSONIC FLOW STRUCTURE IN A COMPLEX FLAT DUCT

M.A. Kotov

,

I.A. Kryukov

,

L.B. Ruleva

,

S.I. Solodovnikov

,

S.T. Surzhikov

Institute for Problems in Mechanics of the Russian Academy of Sciences

e-mail:

mikhail_kotov88@mail.ru

;

kryukov@ipmnet.ru; ruleva@ipmnet.ru

;

sis63@yandex.ru

;

surg@ipmnet.ru

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.

Keywords

:

shock tube, experimental investigation, hypersonic flows, shockwave

mathematical modelling, gas dynamics equations, compressible Navier–Stokes

equations, finite volume approach.

Problem description

. Intensive physical processes near the surface of

the aerospace and hypersonic aircraft (HA) justify the investigation of high-

speed and high-temperature gas flows normally accompanied by a multitude

of non-linearly related physical processes, which stipulates a complex

approach drawing both on the physical experiment and corresponding

computational models.

Such investigations require physical processes data obtained from

(geometrically-) scaled model testing in a shock tube [1]. These setups are

a fairly convenient tool for a wide range of aerodynamics and physical

dynamics problems and enable validation of numerical methods. Short

duration of gas dynamics processes in the shock tube working path

which complicates measurements is canceled out by low-inertia sensors,

noncontact measuring equipment (shadow column devices, interferometers)

[2–4] based on optical instruments and new generation high-speed recording

and processing equipment.

This paper presents the results of the experimental and numerical

investigation of shockwave patterns as a result of hypersonic flow past

HA elements. Aerodynamic models of the following flat duct types were

studied:

4 ISSN 0236-3941. HERALD of the BMSTU. Series “Mechanical Engineering”. 2015. No. 1