Mathematical modeling of the processes of air gas thermodynamics of the supersonic aircraft with a ramjet

1Timoshenko, VI, 1Galinskiy, VP
1Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine, Dnipropetrovsk, Ukraine
Space Sci. & Technol. 2020, 26 ;(2):03-18
Publication Language: Russian
The main issues of the development of design and methodological support for carrying out operational integrated calculations of thermogasdynamic processes in the components of a ramjet engine, integrated with the body of the aircraft, are discussed. The numerical simulation of the flow in a ramjet engine is divided into three components - flow past the aircraft body, flow in the air intake device (AID), the combustion chamber and the nozzle with the exhaust stream. The calculation of supersonic flow near the body of the aircraft, in the entrance part of the AID and in the exhaust jet is carried out in the non-viscous approximation using the Godunov scheme or taking into account the viscosity using the “viscous layer” model. In the region of subsonic flow in the output part of the AID and subsonic nonequilibrium flow in the combustion chamber is calculated using the “narrow channel” model or in the quasi-one-dimensional approximation. The issues of selecting the geometric parameters of the combustion chamber and the near-critical part of the exit nozzle in the case of setting the flow parameters at the outlet of the AID are discussed. The analysis of various models of ignition and combustion of kerosene in the combustion chamber is accomplished. The flow in the exhaust jet is calculated taking into account the flow past the lower tail portion of the surface of aircraft and the interaction of the jet with a disturbed incoming flow of air. Presents the results of the estimated two dimension calculations of individual elements and the complete layout of the stylized aircraft.
Keywords: air intake device, aircraft, combustion chamber, exhaust jet, kerosene combustion, marching calculation methods, nozzle, operational numerical calculation, ramjet, thermogasdynamic processes
1. Artemov O. A. (2006). Ramjet engines (calculation of characteristics). M.: Kompanija Sputnik+ [in Russian].
2. Borisov A. D., Vasjutichev A. S., Laptev I. V. (2018). To the choice of parameters of a ramjet engine, providing a given mode of the main flight of the aircraft. Trudy MAI, Nо. 100. URL: (Last accessed: 09.07.2019) [in Russian].
3. Gun’ko Ju. P., Mazhul’ I. I. (1995). Integrated aero-gas dynamics of hypersonic aircraft with ramjet engines with supersonic combustion. Teplofizika i ajeromehanika, 3, No. 4, 309—321 [in Russian].
4. Gutov B. I., Zvegincev V. I., Mel’nikov A. Ju. (2017). The effect of heat supply in the combustion chamber on the flow in the diffuser of a supersonic air intake. Vestnik Permskogo nacional’nogo issledovatel’skogo politehnicheskogo universiteta. Ajerokosmicheskaja tehnika, Nо. 50, 15—25 [in Russian].
5. Zhukov V. T., Manukovskij K. V., Novikova N. D., Rykov Ju. G., Fedoritova O. B. (2015). Study of the current pattern in the model tract of a high-speed aircraft engine. Preprint IPM im. M. V. Keldysha, Nо. 5, 23 p. [in Russian].
6. Karasev V. N., Levin V. M. (2013). Simulation of ramjet propulsion characteristics for high supersonic flight speeds. Trudy MAI, Nо. 64. URL: (Last accessed: 09.07.2019) [in Russian].
7. Kovenja V. M., Tarnavskij G. A., Chernyj S. G. (1981). Application of the splitting method in problems of gas dynamics. M.: Nauka [in Russian].
8. Kopchenov V. I., Gus’kov O. V. (2011). On the formation of the combustion regime and gas-dynamic structure of the flow in the channel for supersonic conditions at the inlet. Vestnik Nizhegorodskogo universiteta im. N. I. Lobachevskogo, Nо. 4(5), 2260—2262 [in Russian].
9. Lapin Ju. V., Strelec M. H. (1989). Internal flow of gas mixtures. M.: Nauka [in Russian].
10. Levin V. M. (2010). Problems of workflow organization in the ramjet. Fizika gorenija i vzryva, 46, Nо. 4, 45—55 [in Russian].
11. Rogov B. V., Sokolova I. A. (2002). Overview of viscous internal flow patterns. Matematicheskoe modelirovanie. 14, Nо. 1, 87—96 [in Russian].
12. Timoshenko V. I. (2013). Theoretical foundations of technical gas dynamics. Kiev: Naukova dumka [in Russian].
13. Timoshenko V. I. (2019). Homogeneous algorithm for calculating the flow of a viscous supersonic jet into a submerged space. Tehnicheskaja mehanika, Nо. 1, 16—24 [in Russian].
14. Timoshenko V. I., Belocerkovec I. S., Galinskij V. P. (2006). Conceptual issues of mathematical modeling of processes of aerogasothermodynamics of a hypersonic aircraft with a ramjet engine. Ajerogidrodinamika: problemy i perspektivy: sb. nauch. trudov, Nо. 2, 161—181 [in Russian].
15. Timoshenko V. I., Galinskij V. P. (2017). Features of the algorithms for calculating the flow in the air intake channel with backpressure. Tehnicheskaja mehanika, Nо. 3, 16—22 [in Russian].
16. Timoshenko V. I., Gusynin V. P. (1999). The use of hypersonic technology in the creation of advanced transport space systems. Kosmicheskaja nauka i tehnologii, 5, Nо. 1, 87—107 [in Russian].
17. Timoshenko V. I., Deshko A. E. (2015). To the question of the rational organization of the processes of mixing and burning in the combustion chamber of a ramjet. Aviacionno-kosmicheskaja tehnika i tehnologija, Nо. 8 (125), 75—81 [in Russian].
18. Choi J. Y. (2011). A Quasi Global Mechanism of Kerosene Combustion for Propulsion. 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit (31 July — 03 August 2011). San Diego, California, 2011. AIAA-5853.pdf.
19. Gear C. W. (1971). Numerical Initial Value Problems in Ordinary Differential Equations. New Jersey: Prentice-Hall, Inc. Englewood Cliffs. 220 p.