Research progress of the flow and combustion organization for the high-Mach-number scramjet: From Mach 8 to 12

Progress in Aerospace Sciences, Journal Year: 2025, Volume and Issue: unknown, P. 101094 - 101094

Published: March 1, 2025

Language: Английский

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Progress and prospects of artificial intelligence development and applications in supersonic flow and combustion

Progress in Aerospace Sciences, Journal Year: 2024, Volume and Issue: unknown, P. 101046 - 101046

Published: Oct. 1, 2024

Language: Английский

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Experimental study on dynamic characteristics of shock train in an isolator with different types of incident shocks

Physics of Fluids, Journal Year: 2024, Volume and Issue: 36(7)

Published: July 1, 2024

The hypersonic mixed-compression inlet, operating in an off-design state, can be categorized into low-speed and over-speed regimes based on whether the external compression shock is incident internal flow channel. In this study, we investigate movement process of train within inlet/isolator under both conditions by generating various shocks using wedges installed a direct-connected ground wind tunnel. Experimental investigations are conducted to examine dynamic characteristics isolator subjected different types at incoming Mach number 2.7. findings reveal that varying levels backpressure resistance for observed with shocks. Through trajectory leading (STLS) power spectral density analysis, it found unilateral result more intense oscillation lower dominant frequency. mode decomposition method identifies structures unsteady field highlights energy primarily concentrates STLS, while its symmetry influenced type shock. Specifically, symmetric bilateral tends promote higher degree STLS structure reducing strength; however, when passes over reflection point shock, rapid upstream still occurs situation, thereby inducing inlet unstart compromising engine safety.

Language: Английский

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Research on Integrated Design Method of Wide-Range Hypersonic Vehicle/Engine Based on Dynamic Multi-Objective Optimization

Aerospace Science and Technology, Journal Year: 2025, Volume and Issue: 159, P. 110031 - 110031

Published: Feb. 7, 2025

Language: Английский

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An Investigation on Bleed Flow Control of an Axisymmetric Supersonic Intake Based on Parametric Outline Optimization Design

Aerospace Science and Technology, Journal Year: 2025, Volume and Issue: 159, P. 110027 - 110027

Published: Feb. 7, 2025

Language: Английский

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Conceptual design methodology and performance evaluation of turbine-based combined cycle inward-turning inlet with twin-design points

Aerospace Science and Technology, Journal Year: 2024, Volume and Issue: 152, P. 109309 - 109309

Published: June 12, 2024

Language: Английский

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Cooling Characteristics of Opposing Jet-Transpiration Cooling Combined System with Variable Mass Flow Rate Distribution

Aerospace Science and Technology, Journal Year: 2025, Volume and Issue: unknown, P. 110073 - 110073

Published: Feb. 1, 2025

Language: Английский

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Effects of Installation Location on the Performance of a Hypersonic 2D Inlet

Smart innovation, systems and technologies, Journal Year: 2025, Volume and Issue: unknown, P. 389 - 401

Published: Jan. 1, 2025

Language: Английский

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The control mechanism of micro-vortex generators on streamwise vortex-shock train coupling interference

Aerospace Science and Technology, Journal Year: 2025, Volume and Issue: unknown, P. 110308 - 110308

Published: May 1, 2025

Language: Английский

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Quantification of geometric uncertainty on hypersonic aerodynamics in scramjet inlets

Physics of Fluids, Journal Year: 2024, Volume and Issue: 36(9)

Published: Sept. 1, 2024

Geometric deviations arising from manufacturing and assembly processes can significantly impact the aerodynamic stability of scramjet inlets. This study aims to quantify uncertainty sensitivity inlet aerodynamics caused by geometric deviations. Specifically, three representative operating modes are considered: start, half-start, unstart. Five parameters extracted as random uncertain variables, including first second ramp angle (α1, α2), horizontal vertical distance between lip point throat (dh, dv), inner cowl (α3). To achieve quantification objective, non-intrusive polynomial chaos method is employed for quantification. Sobol indices utilized assess each parameter on quantities interest. Results indicate that only ±1% have a significant performance inlet. pressure in shock region more than four times non-shock region, exceeding 40%. With respect parameters, mass capture ratio demonstrates high deviations, with 6.76%. Sensitivity analysis indicates primary factors affecting within isolator dv, α2, dh. Therefore, their should be strictly controlled.

Language: Английский

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