Ionova, I. A.

Maslov, Evgeny Anatolievich

Zolotorev, N. N.

Electronic archive of Tomsk Polytechnic University

21th International conference «MODERN TECHNIQUE AND TECHNOLOGIES» Session 5. PHYSICAL METHODS IN SCIENCE AND ENGINEERING 156 THE EXPERIMENTAL RESEARCH OF HYPERSONIC FLOW  AROUND RAMJET ENGINE MODELS 1Ionova I.A., 1,2Maslov E.A., 2Zolotorev N.N. Scientific Supervisor: Maslov E.A. 1National Research Tomsk Polytechnic University,  Russia, Tomsk, Lenin str., 30, 634050 2Research Institute of Applied Mathematics and Mechanics of Tomsk State University,  Russia, Tomsk, Lenin str. 36, Building 27, 634050 E-mail: irina2.92@mail.ru  ЭКСПЕРИМЕНТАЛЬНОЕ ИССЛЕДОВАНИЕ ГИПЕРЗВУКОВОГО ОБТЕКАНИЯ МОДЕЛЬНЫХ РПД 1Ионова И.А., 1,2Маслов Е.А., 2Золоторев Н.Н. Научный руководитель: Маслов Е.А., к.ф.-м.н., доцент 1Национальный исследовательский Томский политехнический университет, Россия, г.Томск, пр. Ленина, 30, 634050 2Научно-исследовательский институт прикладной математики и механики Национального исследовательского Томского государственного университета Россия, г.Томск, пр. Ленина, 36, стр. 27 634050 E-mail: irina2.92@mail.ru  Recently, an increasing interest in rocket-ramjet engines (RRE), which combines the advantages of solid-fuel and jet engines [1]. The geometrical characteristics of the flow channel changes due to burnout of the solid charge in the process of the operation of the rocket-ramjet engine. Law burning rate of solid fuel in a flow of air is one of the main factors which influence the intra-ballistics characteristics of a rocket-ramjet engine. In this connection, the definition the fields of temperature, pressure, and rate of blowing flow in the flow channel of the engine is an important stage in the designing of rocket-ramjet engines. Mathematical modeling of dynamics and heat transfer in the flow channel of the rocket-ramjet engine allows you to get information about the structure of the flow, about the distribution of gas-dynamic parameters along the channel taking into account changes of its geometric characteristics due to burnout of solid fuel. It is expedient performing of comparative analysis of the numerical results and the experimental data, obtained in models of rocket-ramjet engine, for assess the adequacy of the developed mathematical models. The results of an experimental research of the structure and the basic parameters of the air flow in the flow channel of a flat and an axisymmetric models of rocket-ramjet engine are presented in this paper. TECHNIQUE OF EXPERIMENTAL RESEARCH Experiments for a flat model of engine (Fig. 1) and an axisymmetric model of engine  (Fig. 2) for the measurement of a temperature and a pressure, and for air flow visualization were performed in the range of Mach numbers M = (1÷7) and in the range of stagnation temperatures of free-stream air flow T0 = (20÷500)°C. The experiments were performed on a model aerodynamic stand [2], which allows you to explore the actual processes in the conditions of work of rocket-ramjet engine in the open air at atmospheric pressure. The main function of the aerodynamic stand is create a supersonic impulse gas flow for perform aerodynamic and aero-physics research. Preheating a working gas to 500 °C was realised with use of Cowper-type heater, consisting of a power pipeline and of set of heat-retaining plates. 21th International conference «MODERN TECHNIQUE AND TECHNOLOGIES» Session 5. PHYSICAL METHODS IN SCIENCE AND ENGINEERING 157  Fig. 1. Photos of flat model of rocket-ramjet engine  Fig. 2. Photos axisymmetric model of rocket-ramjet engine Parameters of free-stream air flow, such as rate, static pressure, static temperature, density and Mach number are determined by values of the parameters of air in the prechamber (braking parameters) pf, Tf, ρf  and of the expansion nozzle of aerodynamic stand.  The pressure in the prechamber during experiments were measured by sensor ДМ 5007А – ДИ У2. Combined receiver of pressure, capable of measuring dynamic and static pressure contemporaneously, was installed in the flow channel of the rocket-ramjet engine for determine the Mach number.  Mach number can be determined using gas dynamic functions by the formula:     12 2 2202 141 1 M2 1M1 1kkkkk kpk kpk k      ,  where p, p0 are static and dynamic pressure in the flow, respectively; k is the adiabatic index of gas. Stagnation temperature T0 in the flow channel of models under a heated flow air was measured with a chromel-copel thermocouple junction with diameter of 0,2 mm. Thermocouple was placed on the axis of symmetry of the flow channel near the initial section.   21th International conference «MODERN TECHNIQUE AND TECHNOLOGIES» Session 5. PHYSICAL METHODS IN SCIENCE AND ENGINEERING 158 THE RESULTS OF EXPERIMENTAL RESEARCH Shown in Fig. 3 results of measurements of pressure in the prechamber (a), dynamic (b) and static pressure (c), and the stagnation temperature (d) in the flow channel of an axially symmetric model of rocket-ramjet engine for Mach number Мin = 5 (M5 nozzle).      a) b)       c) d)  Fig. 3. Measurement results In the present experiment using model aerodynamic stand, the calculated value of the Mach number in the flow path of an axially symmetric model rocket-ramjet engine is М = 1,87. CONCLUSION Analysis of visualized flow structure showed that the flow with a set of oblique shocks develops in the flow channel of rocket-ramjet engine models for regimes of flow which are realized. Obtained for models of rocket-ramjet engine experimental data on the structure and basic parameters of the air flow in the flow channel are objective information for mathematical modeling of intrachamber processes. This research was supported by the Ministry of Education and Science of the Russian Federation under the Federal Target Program "Research and development on priority directions of scientific-technological complex of Russia for 2014-2020", the agreement № 14.578.21.0034, unique identifier PNI RFMEFI57814X0034  REFERENCES: 1.   Orlov B.V., Mazing G.Y., Reidel A.L., at al. Basics of designing rocket-ramjet engines for unmanned aerial vehicles. – M.: Mashinostroenie, 1967. – 424 p. 2.   Zvegintsev V.I. Gaz-dynamic installations of short-time acting, 1, Installations for scientific research. – N.: Parallel, 2014, – 551 p. 

Экспериментальное исследование гиперзвукового обтекания модельных РПД

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