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Journal articles on the topic 'Supersonic inlets'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 July 2025

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1

Kazula, Stefan, Mark Wöllner, and Klaus Höschler. "Identification of efficient geometries for variable pitot inlets for supersonic transport." Aircraft Engineering and Aerospace Technology 92, no. 7 (2020): 981–92. http://dx.doi.org/10.1108/aeat-11-2019-0228.

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Purpose This paper aims to reveal the influence of selected geometric parameters on the aerodynamic performance of circular variable aero engine inlets in transonic and supersonic civil aviation. Design/methodology/approach The trade-off in inlet design and aerodynamic evaluation parameters is presented. The approach to investigate the dependencies between the aerodynamic and geometric parameters at different flight conditions by means of a parametric design study is introduced. Findings The dependencies of inlet drag and efficiency from geometric parameters at flight speeds of Mach 0.95 up to

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2

Kazula, Stefan, Mark Wöllner, David Grasselt, and Klaus Höschler. "Parametric Design Study on Aerodynamic Characteristics of Variable Pitot Inlets for Transonic and Supersonic Civil Aviation." MATEC Web of Conferences 304 (2019): 02017. http://dx.doi.org/10.1051/matecconf/201930402017.

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This paper reveals the influence of selected geometric parameters on the aerodynamic performance of circular variable aero engine inlets in transonic and supersonic civil aviation. The trade-off in inlet design and aerodynamic evaluation parameters are presented. The approach to investigate the dependencies between the aerodynamic and geometric parameters at different flight conditions by means of a parametric design study is introduced. The dependencies of inlet drag and efficiency from geometric parameters at flight speeds of Mach 0.95 up to Mach 1.6 are identified. Although entailing additi

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3

Argrow, B. M., and G. Emanuel. "Computational Analysis of the Transonic Flow Field of Two-Dimensional Minimum Length Nozzles." Journal of Fluids Engineering 113, no. 3 (1991): 479–88. http://dx.doi.org/10.1115/1.2909521.

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The method of characteristics is used to generate supersonic wall contours for two-dimensional, straight sonic line (SSL) and curved sonic line (CSL) minimum length nozzles for exit Mach numbers of two, four and six. These contours are combined with subsonic inlets to determine the influence of the inlet geometry on the sonic-line shape, its location, and on the supersonic flow field. A modified version of the VNAP2 code is used to compute the inviscid and laminar flow fields for Reynolds numbers of 1,170, 11,700, and 23,400. Supersonic flow field phenomena, including boundary-layer separation

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4

Wang, Yuhui, Junhua Zhang, Zhaoyang Tian, and Lei Shi. "Freejet tests on a variable geometry supersonic inlet driven by shape memory alloys." Journal of Physics: Conference Series 3041, no. 1 (2025): 012007. https://doi.org/10.1088/1742-6596/3041/1/012007.

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Abstract Conventional variable geometry supersonic inlets have defects of high redundant mass, large size and poor control effect. A variable geometry inlet with the SMAs as the control element is experimentally studied in a high-speed wind tunnel. The control scheme for inlet shapes is proposed, and the operating characteristics of the variable geometry inlet under typical conditions have been examined. The deformation of the throat and forebody can ensure stable operation of the inlet in a wide flight Mach number domain.

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5

Lee, Hyoung Jin, Bok Jik Lee, Sung Don Kim, and In-Seuck Jeung. "Flow Characteristics of Small-Sized Supersonic Inlets." Journal of Propulsion and Power 27, no. 2 (2011): 306–18. http://dx.doi.org/10.2514/1.46101.

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6

Safarik, Pavel, and Arnold Polak. "Optimal shock wave parameters for supersonic inlets." Journal of Propulsion and Power 12, no. 1 (1996): 202–5. http://dx.doi.org/10.2514/3.24011.

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7

Pordal, H. S., P. K. Khosla, and S. G. Rubin. "Transient behavior of supersonic flow through inlets." AIAA Journal 30, no. 3 (1992): 711–17. http://dx.doi.org/10.2514/3.10976.

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8

Kazula, S., and K. Höschler. "Review of variable leading-edge patents for aircraft wings and engine inlets and their relevance for variable pitot inlets in future supersonic transport." CEAS Aeronautical Journal 12, no. 3 (2021): 685–700. http://dx.doi.org/10.1007/s13272-021-00520-y.

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AbstractThe motivation for designing variable pitot inlets for future supersonic transport (SST) is explained. A comprehensive overview of existing technological solutions for variable leading edges of aircraft wings and engine inlets is given. The advantages and limitations of over 80 solutions, as well as their relevance for application on variable pitot inlets for SST are described. The challenges of existing solution options concerning design methodologies, level of detail, and experience with a technology are identified.

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9

Vinogradov, Viacheslav A., Yurii M. Shikhman, and Corin Segal. "A Review of Fuel Pre-injection in Supersonic, Chemically Reacting Flows." Applied Mechanics Reviews 60, no. 4 (2007): 139–48. http://dx.doi.org/10.1115/1.2750346.

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Developing an efficient, supersonic combustion-based, air breathing propulsion cycle operating above Mach 3.5, especially when conventional hydrocarbon fuels are sought and particularly when liquid fuels are preferred to increase density, requires mostly effective mechanisms to improve mixing efficiency. One way to extend the time available for mixing is to inject part of the fuel upstream of the vehicle’s combustion chamber. Injection from the wall remains one of the most challenging problems in supersonic aerodynamics, including the requirement to minimize impulse losses, improve fuel-air mi

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10

Kazula, Stefan, Marcel Mischke, Paul König, and Klaus Höschler. "Evaluation of Variable Pitot Inlet Concepts for Transonic and Supersonic Civil Aviation." MATEC Web of Conferences 304 (2019): 02016. http://dx.doi.org/10.1051/matecconf/201930402016.

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This paper describes the selection of the ideal variable inlet concept group by utilising results of aerodynamic investigations, system safety analyses and integration studies. Aerodynamic and functional inlet requirements are explained, and variable inlet concept groups are introduced. The concept evaluation by means of a weighted point rating is presented. The respective concept groups are analysed and evaluated regarding economic, functional and safety requirements. By means of this evaluation, the concept group that adjusts the inlet geometry by rigid segment repositioning is identified as

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11

Galkin, V. M., V. I. Zvegintsev, and D. A. Vnuchkov. "Investigation of annular supersonic inlets with isentropic compression." Thermophysics and Aeromechanics 23, no. 5 (2016): 645–55. http://dx.doi.org/10.1134/s0869864316050036.

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12

Xie, Wen-zhong, Yan Ge, Hao Chen, Yu-fen Wen, and S. M. Guo. "Rapid supersonic performance prediction for 2D ramjet inlets." Aerospace Science and Technology 53 (June 2016): 220–31. http://dx.doi.org/10.1016/j.ast.2016.03.025.

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13

Tamilselvam, Nallusamy, A.A.Aswini, P.Varalakshmi, G.P.Clastinmony, and B.Malarvizhi. "Design of Diverter less Supersonic Bifurcating Inlet for Increased Thrust and Stealth Characteristics in High Speed Fighter Aircraft." International Journal of Applied Engineering Research, ISSN 0973-4562 Vol. 10, No.55 (2015): 3975–77. https://doi.org/10.5281/zenodo.5115777.

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The necessity of Fighter Aircrafts to travel faster than the speed of sound has resulted in the development of more complex and sophisticated inlet designs for modern-day fighters. Depending on the plication various types of Supersonic inlet configurations such as Pitot intake, Bellmouth Intake, Serpentine Intakes, etc., are used. The design of a simple supersonic intake is strongly dependent upon the Total Pressure Recovery and the flow uniformity at the face of the compressor. The present study is focused on the design and analysis of Diverter less Supersonic Bifurcating Inlet for and their

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14

Kazula, Stefan, and Klaus Höschler. "Evaluation of variable pitot inlet concepts for transonic and supersonic civil aviation." Aircraft Engineering and Aerospace Technology 92, no. 6 (2020): 807–15. http://dx.doi.org/10.1108/aeat-11-2019-0225.

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Purpose This paper aims to describe the selection of the ideal variable inlet concept group by using results of aerodynamic investigations, system safety analyses and integration studies. Design/methodology/approach Aerodynamic and functional inlet requirements are explained and variable inlet concept groups are introduced. The concept evaluation by means of a weighted point rating is presented. The respective concept groups are analysed and evaluated regarding economic, functional and safety requirements. Findings By means of this evaluation, the concept group that adjusts the inlet geometry

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15

Ferrero, Andrea. "Control of a Supersonic Inlet in Off-Design Conditions with Plasma Actuators and Bleed." Aerospace 7, no. 3 (2020): 32. http://dx.doi.org/10.3390/aerospace7030032.

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Supersonic inlets are a key component of present and future air-breathing propulsion systems for high-speed flight. The inlet design is challenging because of several phenomena that must be taken under control: shock waves, boundary layer separation and unsteadiness. Furthermore, the intensity of these phenomena is strongly influenced by the working conditions and so active control systems can be particularly useful in off-design conditions. In this work, a mixed compression supersonic inlet with a double wedge ramp is considered. The flow field was numerically investigated at different values

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16

Sun, Bo, and Kun-yuan Zhang. "Empirical Equation for Self-starting Limit of Supersonic Inlets." Journal of Propulsion and Power 26, no. 4 (2010): 874–75. http://dx.doi.org/10.2514/1.46798.

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17

Blaize, Michael, Doyle Knight, and Khaled Rasheed. "Automated Optimal Design of Two-Dimensional Supersonic Missile Inlets." Journal of Propulsion and Power 14, no. 6 (1998): 890–98. http://dx.doi.org/10.2514/2.5382.

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18

Gaiddon, Arnaud, and Doyle D. Knight. "Multicriteria Design Optimization of Integrated Three-Dimensional Supersonic Inlets." Journal of Propulsion and Power 19, no. 3 (2003): 456–63. http://dx.doi.org/10.2514/2.6129.

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19

Zou, Jiarui, Xiaoqiang Fan, and Bing Xiong. "Effect of expansion waves on the interaction between dual separation zones." Journal of Physics: Conference Series 3026, no. 1 (2025): 012052. https://doi.org/10.1088/1742-6596/3026/1/012052.

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Abstract Commonly, multiple separation zones exist in hypersonic inlets, inducing instability and energy loss, which are unexcepted during the flight. To solve this issue, lots of investigations have been conducted on the shock wave/boundary layer interaction, and numerous theories have been established. However, the existing theories on single shock wave/boundary layer interaction cannot fully explain the complex phenomenon that occurred in hypersonic inlets under the effect of background waves. A simplified dual-separation-zone model is extracted from the inlet flow field, and a series of si

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20

Qiushi, Li, Lv Yongzhao, and Li Shaobin. "A quasi one-dimensional bleed flow rate model for terminal normal shock stability in mixed compression supersonic inlet." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 228, no. 14 (2014): 2569–83. http://dx.doi.org/10.1177/0954406213519975.

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Ninety-degree (normal) bleed slots have been used to stabilize the terminal normal shock in the throat of a mixed compression supersonic inlet. In this study, a quasi-one-dimensional bleed flow rate model, consisting of a constant-area channel with a pair of normal slots symmetrically located along the upper and lower endwalls, is developed. The bleed flow rate is shown to be a function of the terminal normal shock position within the slot. Some key factors, such as the bleed discharge coefficient, taken from the Bragg model, were derived from the basic laws of conservation for a one-dimension

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21

Chen, Yanjun. "Shock Wave-Boundary Layer Interaction: A Survey of Recent Development." Highlights in Science, Engineering and Technology 112 (August 20, 2024): 422–30. http://dx.doi.org/10.54097/smvame92.

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This paper reviews the latest research advancements in shock wave boundary layer interactions. These interactions are crucial in aerospace engineering, particularly in design of hypersonic vehicle inlets, flow control, and thermal protection systems. The paper first revisits the fundamental physical phenomena and theoretical models of SWBLI, then delves into recent experimental and numerical studies under various flow conditions, including supersonic inlets, turbomachinery, the effects of expansion waves, and the impact of roughness elements. Through an analysis of these research findings, we

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22

Slater, John W. "Improvements in Modeling 90-degree Bleed Holes for Supersonic Inlets." Journal of Propulsion and Power 28, no. 4 (2012): 773–81. http://dx.doi.org/10.2514/1.b34333.

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23

Ran, Hongjun, Russell Deany, and Dimitri N. Mavris. "Determination of the Terminal Shock in Two-Dimensional Supersonic Inlets." Journal of Aircraft 49, no. 5 (2012): 1532–35. http://dx.doi.org/10.2514/1.c031736.

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24

Slater, John W., and John D. Saunders. "Modeling of Fixed-Exit Porous Bleed Systems for Supersonic Inlets." Journal of Propulsion and Power 26, no. 2 (2010): 193–202. http://dx.doi.org/10.2514/1.37390.

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25

Kapoor, K., T. G. Pai, and B. N. Pamadi. "Subcritical flow studies on two-dimensional external compression supersonic inlets." Journal of Propulsion and Power 8, no. 4 (1992): 849–56. http://dx.doi.org/10.2514/3.23559.

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26

Saheby, Eiman B., Huang Gouping, and Anthony Hays. "Design of top mounted supersonic inlets for a cylindrical fuselage." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 8 (2018): 2956–79. http://dx.doi.org/10.1177/0954410018790173.

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Designing an inlet based on the fuselage geometry and its constraints is an important part of flight vehicle design. Among the different possible configurations, design integration of a supersonic inlet with a cylindrical fuselage is a major challenge. On one hand, propulsive efficiency requirements force the designers to consider the simplest compression surfaces for the inlet entrance geometries and on the other hand, the considerable drag of inlet/diverter integrations needs to be minimized, which can affect the inlet. In this paper, two new concepts as a replacement for a top mounted pitot

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27

Prasad, Dilip, and Jinzhang Feng. "Propagation and Decay of Shock Waves in Turbofan Engine Inlets." Journal of Turbomachinery 127, no. 1 (2005): 118–27. http://dx.doi.org/10.1115/1.1811102.

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Numerical experiments are carried out to investigate the tone noise radiated from a turbofan engine inlet under conditions at which the relative flow past the rotor tip is supersonic. Under these conditions, the inlet tone noise is generated by the upstream-propagating rotor-locked shock wave field. The spatial evolution of this shock system is studied numerically for flows through two basic hard-walled configurations: a slender nacelle with large throat area and a thick nacelle with reduced throat area. With the flight Mach number set to 0.25, the spatial evolution of the acoustic power throu

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28

Venkatakrishnan, L., and A. Krothapalli. "Forward Flight Effects on Fan Noise from Supersonic 2-D Inlets." Journal of Aircraft 43, no. 5 (2006): 1549–51. http://dx.doi.org/10.2514/1.18264.

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29

Zvegintsev, V. I. "Gas-dynamic problems in off-design operation of supersonic inlets (review)." Thermophysics and Aeromechanics 24, no. 6 (2017): 807–34. http://dx.doi.org/10.1134/s0869864317060014.

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30

Detwiler, K. P., Z. Yuan, and W. F. Ng. "Experimental and numerical studies of the aeroacoustics of axisymmetric supersonic inlets." Journal of Sound and Vibration 184, no. 5 (1995): 853–70. http://dx.doi.org/10.1006/jsvi.1995.0349.

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31

Kobayash, Hiroaki, Yusuke Maru, Motoyuki Hongoh, Shinsuke Takeuchi, Keiichi Okai, and Takayuki Kojima. "Study on variable-shape supersonic inlets and missiles with MRD device." Acta Astronautica 61, no. 11-12 (2007): 978–88. http://dx.doi.org/10.1016/j.actaastro.2006.12.018.

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32

Freskos, G., and O. Penanhoat. "Numerical Simulation of the Flow Field Around Supersonic Air-Intakes." Journal of Engineering for Gas Turbines and Power 116, no. 1 (1994): 116–23. http://dx.doi.org/10.1115/1.2906780.

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The demand for efficiency in today’s and in future civil aircraft is such that experimental studies alone do not suffice to optimize aircraft aerodynamics. In this context, much effort has been spent in the past decade to develop numerical methods capable of reproducing the phenomena that occur in the engine flow field. This paper presents some studies in Computational Fluid Dynamics related to supersonic inlets. Two approaches are considered. First, there is a need for a code capable of calculating in a cost-efficient way the entire flow field around a two-dimensional or three-dimensional inl

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33

Haws, Richard G., Jeff S. Noall, and Russell L. Daines. "Computational Investigation of a Method to Compress Air Fluidically in Supersonic Inlets." Journal of Spacecraft and Rockets 38, no. 1 (2001): 51–59. http://dx.doi.org/10.2514/2.3654.

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34

Goonko, Yu P., and I. I. Mazhul. "Design of supersonic three-dimensional inlets using two-dimensional isentropic compression flow." Thermophysics and Aeromechanics 18, no. 1 (2011): 87–100. http://dx.doi.org/10.1134/s0869864311010100.

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35

Yunsong, Jiang, Gao Zhenxun, and Jiang Chongwen. "Study on the Design of Supersonic Axisymmetric Multicompression and Quasi-isentropic Inlets." Procedia Engineering 99 (2015): 530–35. http://dx.doi.org/10.1016/j.proeng.2014.12.567.

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36

Berra, Lee M., John W. Slater, and Semih M. Olcmen. "Conceptual redesign of the B-1B bomber inlets for improved supersonic performance." Aerospace Science and Technology 45 (September 2015): 476–83. http://dx.doi.org/10.1016/j.ast.2015.06.017.

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37

Kim, Sang Dug, and Dong Joo Song. "Numerical study on performance of supersonic inlets with various three-dimensional bumps." Journal of Mechanical Science and Technology 22, no. 8 (2008): 1640–47. http://dx.doi.org/10.1007/s12206-008-0503-9.

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38

Sun, Fengyong, Jitai Han, and Changpo Song. "A Novel Approach to High Stability Engine Control for Aero-Propulsion Systems in Supersonic Conditions." Aerospace 11, no. 12 (2024): 1029. https://doi.org/10.3390/aerospace11121029.

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In a supersonic state, the aero-engine operates under harsh circumstances of elevated temperature, high pressure, and rapid rotor speed. This work provides an innovative high-stability control technique for engines with fixed-geometry inlets, addressing stability control issues at the aero-propulsion system level. The discussion begins with the importance of an integrated model for the intake and the aero-engine, introducing two stability indices (surge margin and buzz margin) to characterize inlet stability. A novel predictive model for engine air mass flow is developed to address the indeter

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39

Forney, L. J., W. K. McGregor, and D. B. Van Dyke. "Computation of Gas Flowfields in Supersonic Particle Probes." Journal of Fluids Engineering 108, no. 1 (1986): 76–81. http://dx.doi.org/10.1115/1.3242547.

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The results of computations to predict the properties of gas flowfields in supersonic particle probe inlets are presented. In particular, a supersonic gas impinging on a thin walled cylindrical probe aligned parallel to the freestream has been analyzed. Inviscid solutions are obtained by a slight variant to MacCormack’s time-dependent finite difference method. Imposing outflow boundary conditions of fixed static pressure at the probe outlet, linear extrapolation of remaining gas properties, and a reflection technique on the probe wall including the tip, reasonable agreement is demonstrated for

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40

Yoshimoto, Shigeka, Makoto Yamamoto, and Kazuyuki Toda. "Numerical Calculations of Pressure Distribution in the Bearing Clearance of Circular Aerostatic Thrust Bearings With a Single Air Supply Inlet." Journal of Tribology 129, no. 2 (2006): 384–90. http://dx.doi.org/10.1115/1.2464135.

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This paper describes the pressure distribution in the bearing clearance of circular aerostatic thrust bearings with a single air supply inlet. For high air supply pressure, large bearing clearance, and a relatively small bearing outer radius, it was believed that shock waves are caused and that a complex fluid flow structure is formed in the bearing clearance. Accordingly, analytical models based on the occurrence of shock wave in the bearing clearance have been proposed. Recently, very small aerostatic bearings have been used in various machine devices where the pressure distribution near the

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41

Malo-Molina, Faure J., Datta V. Gaitonde, Houshang B. Ebrahimi, and Stephen M. Ruffin. "Three-Dimensional Analysis of a Supersonic Combustor Coupled to Innovative Inward-Turning Inlets." AIAA Journal 48, no. 3 (2010): 572–82. http://dx.doi.org/10.2514/1.43646.

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42

Dalle, Derek J., Matt L. Fotia, and James F. Driscoll. "Reduced-Order Modeling of Two-Dimensional Supersonic Flows with Applications to Scramjet Inlets." Journal of Propulsion and Power 26, no. 3 (2010): 545–55. http://dx.doi.org/10.2514/1.46521.

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43

Hamed, A., and J. S. Shang. "Survey of validation data base for shockwave boundary-layer interactions in supersonic inlets." Journal of Propulsion and Power 7, no. 4 (1991): 617–25. http://dx.doi.org/10.2514/3.23370.

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44

Xie, Wen-Zhong, Wei Yang, Yi Jin, Shuzi Yang, Cheng Zeng, and Shengmin Guo. "Prediction of self-starting limit of two-dimensional supersonic inlets considering viscous effects." Aerospace Science and Technology 106 (November 2020): 106229. http://dx.doi.org/10.1016/j.ast.2020.106229.

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45

Krasheninnikov, Sergey Ju, Alexey K. Mironov, Evgeny V. Pavlyukov, Andrey V. Shenkin, and Vladimir K. Zhitenev. "Mixer-Ejector Nozzles: Acoustic and Thrust Characteristics." International Journal of Aeroacoustics 4, no. 3 (2005): 267–88. http://dx.doi.org/10.1260/1475472054771448.

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The paper presents the review of the CIAM/TsAGI investigations of mixer-ejector models, which could be considered to be prototypes of real variable area nozzles for future supersonic aircraft. Acoustic and aerodynamic characteristics of both 2-D and axisymmetrical models were obtained. The influence of nozzle geometry (number of lobes, lobe shape, ejector length, auxiliary inlets in the ejector walls) on its noise and thrust performances is discussed. The experimental data show that the best mixer-ejector configuration tested provides a noise reduction efficiency of about 3 ∼ 3.5 PNdB per 1% t

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46

Aithal, S. M. "Characteristics of optimum power extraction in a MHD generator with subsonic and supersonic inlets." Energy Conversion and Management 50, no. 3 (2009): 765–71. http://dx.doi.org/10.1016/j.enconman.2008.09.037.

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47

Vojta, Lukas, Jan Kracik, and Vaclav Dvorak. "Introductory Numerical Study on Supersonic Ejector Working with R32." EPJ Web of Conferences 213 (2019): 02096. http://dx.doi.org/10.1051/epjconf/201921302096.

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Nowadays, there is an increasing demand for devices which work efficiently with the smallest possible consumption of energy. In this regard, incorporating ejectors seems to be an interesting choice. This paper describes the numerical analysis of the flow in a supersonic ejector working with R32 (difluoromethane) as the working fluid. The ejector geometry under investigation in this paper has already been experimentally analysed, however, air was used as the working fluid. Therefore, this paper deals with a numerical analysis of the same geometry but with a different working fluid. Furthermore,

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48

Zhang, Sheng, Zheng Lin, Zeming Gao, et al. "Wind Tunnel Experiment and Numerical Simulation of Secondary Flow Systems on a Supersonic Wing." Aerospace 11, no. 8 (2024): 618. http://dx.doi.org/10.3390/aerospace11080618.

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Aircraft secondary flow systems are small-flow circulation devices that are used for thermal and cold management, flow control, and energy generation on aircraft. The aerodynamic characteristics of main-flow-based inlets have been widely studied, but the secondary-flow-based small inlets, jets, and blowing and suction devices have seldom been studied. Two types of secondary flow systems embedded in a supersonic aircraft wing, a ram-air intake and a submerged intake, are researched here. Firstly, wind tunnel tests under subsonic, transonic, and supersonic conditions are carried out to test the

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49

Tindell, R. H. "Computational Fluid Dynamic Applications for Jet Propulsion System Integration." Journal of Engineering for Gas Turbines and Power 113, no. 1 (1991): 40–50. http://dx.doi.org/10.1115/1.2906529.

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The impact of computational fluid dynamics (CFD) methods on the development of advanced aerospace vehicles is growing stronger year by year. Design engineers are now becoming familiar with CFD tools and are developing productive methods and techniques for their applications. This paper presents and discusses applications of CFD methods used at Grumman to design and predict the performance of propulsion system elements such as inlets and nozzles. The paper demonstrates techniques for applying various CFD codes and shows several interesting and unique results. A novel application of a supersonic

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50

Syam, S., Gauresh Raj Jassal, and Bryan E. Schmidt. "An Experimental Investigation On The Effect Of Laser Energy Deposition In An Over-Expanded Jet." Proceedings of the International Symposium on the Application of Laser and Imaging Techniques to Fluid Mechanics 21 (July 8, 2024): 1–14. http://dx.doi.org/10.55037/lxlaser.21st.200.

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The shock train structure of a supersonic over-expanded jet is the product of the interaction between the jet flow at the nozzle exit and the ambient environment. Although the effect of flow disturbances on the performance of the supersonic inlets has been studied in detail, a limited understanding of the shock train dynamics subject to flow disturbances is available for over-expanded jets. This experimental investigation focuses on understanding the influence of perturbations due to short-duration energy deposition on the shock train structure and its dynamics in an axisymmetric over-expanded

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