A Multifidelity Simulation Method for Internal and External Flow of a Hypersonic Airbreathing Propulsion System

Liu, Jun; Yuan, Hang; Zhang, Jinsheng; Kuang, Zheng

doi:10.3390/aerospace9110685

Cited by 2 publications

(2 citation statements)

References 22 publications

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“…(4) The propulsion module is used to simulate the flow field of the isolator and combustor using a quasi-one-dimensional model, and to estimate the pressure distribution on the surface of the nozzle using the one-dimensional plume method. (5) The inviscid CFD results of the isolator, combustor, and nozzle from Step 2 are replaced with the results from Step 4 (using the quasi-one-dimensional model). After that, the pressure distribution of the entire aircraft with the engine operating is obtained.…”

Section: Procedures Of the Integrated Aeroproplusive Analysismentioning

confidence: 99%

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A Rapid Method of Integrated Aeropropulsive Analysis for the Conceptual Design of Airbreathing Hypersonic Aircraft

Dai,

Fan,

et al. 2024

Aerospace

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A special feature of airbreathing hypersonic aircraft is the complex coupling between aerodynamic and propulsive performances. This study presents a rapid analysis methodology for the integration of these two critical aspects in the conceptual design of airbreathing hypersonic aircraft. Parametric modeling is used to generate a three-dimensional geometric model of an aircraft. The integrated aerodynamic and propulsive analysis is performed using a loosely coupled method. The aerodynamic analysis uses Euler equations to solve the inviscid aerodynamic forces, while the viscous forces are estimated using semi-empirical engineering methods. The propulsion system is modeled using hybrid one- and three-dimensional approaches. The inlet aerodynamic performance is simulated using three-dimensional simulation based on the Euler equations. The ramjet performance is estimated using a quasi-one-dimensional mathematical model. Nozzle simulation is performed using a one-dimensional plume method. The entire computational process is integrated and can be run automatically. The usefulness of the method is demonstrated through aerodynamic and propulsive performance evaluations in the conceptual design of a notional airbreathing hypersonic aircraft.

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Section: Procedures Of the Integrated Aeroproplusive Analysismentioning

confidence: 99%

“…This kind of aircraft is characterized by the ability to fly over a wide range of speeds, from subsonic to hypersonic, and to traverse vast airspaces from the sea level to near space [3]. Furthermore, airbreathing hypersonic technology plays an important role in reusable space transport systems [4][5][6][7].…”

Section: Introductionmentioning

confidence: 99%

A Rapid Method of Integrated Aeropropulsive Analysis for the Conceptual Design of Airbreathing Hypersonic Aircraft

Dai,

Fan,

et al. 2024

Aerospace

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Reynolds Number Effect on Aerodynamic and Starting Characteristics of a Two-Dimensional Hypersonic Inlet

2022

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The Reynolds number effect induced by model scaling and inflow conditions will affect the aerodynamic and starting characteristics of a two-dimensional hypersonic inlet. This effect is investigated through a numerical simulation method. First, the numerical simulation method is validated through experimental data. The static pressure from the numerical simulation method agreed well with wind tunnel tests. Then, this simulation method is used to study the Reynolds number effect on a two-dimensional hypersonic inlet caused by the model scaling and inflow conditions. The numerical simulation results indicate that as the Reynolds number decreases from 4.86 × 106 to 9.71 × 104 with model scaling increases from 1 to 1/50, the relative boundary layer thickness at the entrance of the inlet increases from 10.4% to 21.2%; as the flight altitude increases from 25.5 km to 36.5 km, which causes the Reynolds number to decrease from 5.67 × 106 to 1.07 × 106, the relative boundary layer thickness at the entrance of the inlet increases from 9.8% to 13.2%. Finally, the Reynolds number effect on the aerodynamics and starting characteristics caused by these two different factors are compared. The results show that the effect of scaling the model is similar to the effect of changing the altitude. As the relative boundary layer thickness increased by 1.0%, the total pressure recovery at the throat section decreased by 0.8%, and the inlet starting Mach number increased by 0.1.

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A Multifidelity Simulation Method for Internal and External Flow of a Hypersonic Airbreathing Propulsion System

Cited by 2 publications

References 22 publications

A Rapid Method of Integrated Aeropropulsive Analysis for the Conceptual Design of Airbreathing Hypersonic Aircraft

A Rapid Method of Integrated Aeropropulsive Analysis for the Conceptual Design of Airbreathing Hypersonic Aircraft

Reynolds Number Effect on Aerodynamic and Starting Characteristics of a Two-Dimensional Hypersonic Inlet

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