Influence of the shape of the subsonic part of the supersonic inlet device on the coefficient of conservation of total pressure

Artem Khorokhordin, Ihor Kravchenko, Mykhailo Mitrakhovych, Kateryna Balalaieva, Vyacheslav Usenko

Abstract


The subject of this study is the total pressure conservation coefficient. The object of this study is the channel of the subsonic part of a supersonic input device of rectangular and oval shape, equivalent in size. The purpose of this study is to study the shape of the subsonic part of a supersonic external compression input device. To achieve this purpose, the following tasks were solved: modeling the flow in the subsonic part of a supersonic inlet external compression input device of rectangular and oval shape; calculation of the total pressure conservation coefficient in the subsonic part of the rectangular and oval supersonic inlet external compression input device. When studying the shape of the subsonic part of the supersonic inlet external compression device, the method of numerical experiment was used. The studies were conducted at an estimated altitude of 12 km and an estimated Mach number M = 2.5. The influence of the fuselage on the operation of the input device was not considered. To study the influence of the cross-sectional shape of the studied subsonic parts of the inlet device, the coefficient of conservation of total pressure in 7 cross sections along the length of the inlet device was calculated. To obtain the initial data for modeling the flow in a subsonic channel, an analytical calculation of the flow parameters in the supersonic part of the input device was performed. The results of flow modeling showed that the total pressure conservation coefficient of the subsonic part of the studied inlet devices when operating at an altitude of 12 km was 0.982 in the subsonic part of the supersonic inlet device with oval sections and 0.993 in the subsonic part of the supersonic inlet device with rectangular sections. The resulting visualization of streamlines in the studied channels demonstrates the presence of a paired vortex formed in the initial section of the channel with oval cross-sections, which leads to significant losses in total pressure. The scientific novelty and practical significance of this study lie in the fact that new data were obtained regarding the comparison of the total pressure conservation coefficient for equivalent subsonic parts of a supersonic oval and rectangular inlet device. Recommendations on the rational form of the subsonic part of the supersonic inlet external compression device were obtained.

Keywords


supersonic external compression inlet device; subsonic channel; narrowing of the canal; channel shape; total pressure conservation coefficient; pair vortex

References


Cizmas, P. G. A. Aerothermodynamics and Jet Propulsion. Cambridge University Press, 2021. 482 p.

El-Sayed, A. F. Fundamentals of Aircraft and Rocket Propulsion. Springer, 2016. 1025 p.

Oates, G. C. Aircraft propulsion systems technology and design. Washington, American Institute of Aeronautics and Astronautics, 1989. 528 p. DOI: 10.2514/4.861499.

Farahani, M., & Mahdavi, M. M. A proposed design method for supersonic inlet to improve performance parameters. Aerospace Science and Technology, 2019, vol. 91, pp. 583-592. DOI: 10.1016/j.ast.2019.05.014.

Watanabe, Y., & Murakami, A. Control of Supersonic Inlet with Variable Ramp. Proceedings of 25th International Congress of the Aeronautical Sciences, ICAS 2006, 2006. 10 p. Available at: https://www.icas.org/ICAS_ARCHIVE/ICAS2006/PAPERS/238.PDF. (accessed 12.12.2023).

Soltani, M. R., Younsi, J. S., Farahani, M., & Masoud A. Numerical Simulation and Parametric Study of Supersonic Intake. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2013, vol. 227, iss. 3, pp. 467-479. DOI: 10.1177/0954410012436620.

Watanabe, Y., Murakami, A., & Fujiwara H. Effect of Sidewall Configuration on the Aerodynamic Performance of Supersonic Air-Intake. 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2002, article no. AIAA 2002-3777. DOI: 10.2514/6.2002-3777.

Liang, Z., Liu, Y., Yang, Yo., Yang, Ya., & Yang, H. Aero-Engine Air Intake and Its Location Design. Journal of Research in Multidisciplinary Methods and Applications, 2022, vol. 1, iss. 1, article no. 01220101001. Available at: http://satursonpublishing.com/jrmma/article/view/a01220101001. (accessed 5.01.2024).

Niaz, F., Zia, U., Masud, J., & Safdar, M. M. Intake Performance Analysis for Extra-Design Variations in Local Flow Field of a Supersonic Aircraft. In AIAA SCITECH 2024 Forum, 2024. DOI: 10.2514/6.2024-0002.

Chen, H., Sun, M., Xiong, D., Yang, Y., Wang, T., & Wang, H. Large eddy simulation of supersonic flow in ducts with complex cross-sections. Theoretical and Applied Mechanics Letters, 2023, vol. 13, iss. 6, article no. 100469. DOI: 10.1016/j.taml.2023.100469.

Singh Sandhu, J. P., Bhardwaj, M., Sharma, A., Ananthkrishnan, N., & Park, I. S. Multi-Objective Optimization of Arbitrary Supersonic Intake Based on Axiomatic Design Theory using Kriging/MOGA. In AIAA AVIATION 2023 Forum, 2023, article no. 4445. DOI: 10.2514/6.2023-4445.

Philippou, A. L., Zachos, P. K., & MacManus, D. G. Aerodynamic Instabilities in High-Speed Air Intakes and Their Role in Propulsion System Integration. Aerospace, 2024, vol. 11, iss. 1, article no. 75. DOI: 10.3390/ aerospace11010075.

EsfandAbadi, M. H. M., Mohammadi, A., & Djavareshkian, M. H. Design and Analysis of Supersonic Inlet for Ramjet Engines: Aerodynamic Considerations and Performance Optimization. Journal of Aerospace Science and Technology, 2024, vol. 17, iss. 1, pp. 47-59. DOI: 10.22034/jast.2023.421137.1165.

Rathakrishnan, E. Introduction to Aerospace Engineering. Basic Principles of Flight. John Wiley & Sons, 2021. 256 p. ISBN: 978-1-119-80686-8.

Hermann, R. Supersonic Inlet Diffusers and Introduction to Internal Aerodynamics. Minneapolis-Honeywell Regulator Company, Aeronautical Division, 1956. 378 p.

Menter, F. R., Kuntz, M., & Langtry, R. Ten years of industrial experience with the SST turbulence model. Turbulence, heat and mass transfer, 2003, vol. 4, pp. 625-632.




DOI: https://doi.org/10.32620/aktt.2024.2.03