Study on modified Crocco’s model for thermodynamic calculation for Dual Mode Ramjet Engine

H.J. NAMKOUNG

DOI Number: XXX-YYY-ZZZ

Conference number: HiSST2024-00359

A pseudo-shock model is proposed, the model makes possible to estimate the distribution of parameters during the transition from a supersonic flow to a subsonic one in the structure of a mathematical model of a supersonic direct-flow propulsion system with deceleration region. A numerical simulation of the gas-dynamic parameters in the channel of the pre-chamber diffuser (isolator) of a given geometry was performed. The numerical solution is obtained using the principle of minimum entropy production. Verification of the proposed model on the data obtained in the course of experimental tests of the combustor of a dual-mode ramjet engine (DMR) has been performed. The model is intended for parametric studies as part of mathematical models of DMR.

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Crocco, Dual Mode Ramjet, Hypersonic, Isolator

In Categories: 1.Events, HiSST 2024, Hypersonic Fundamentals and History

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