A study of a boundary layer trip concept at hypersonic speeds

Nestler, D. E.; Mccauley, William D

doi:10.2514/6.1981-1086

Cited by 6 publications

(1 citation statement)

References 5 publications

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“…The criterion for deciding whether flow separation has occurred in the combustor is assumed to be the same as the one in the inlet [28]:…”

Section: Analysis Methods For Isolator and Combustormentioning

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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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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“…The criterion for deciding whether flow separation has occurred in the combustor is assumed to be the same as the one in the inlet [28]:…”

Section: Analysis Methods For Isolator and Combustormentioning

confidence: 99%