Implementing a Dual-Mode Scramjet Combustor Model in NPSS

Connolly, Brian J.; Krouse, Charles; Musgrove, Grant O.

doi:10.2514/6.2021-3538

Cited by 3 publications

(1 citation statement)

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“…Their work demonstrates the importance of multifidelity and componentintegrated analysis. Owing to the lack of flame blowout prediction capabilities developed by Vijayakumar et al [18] and Vu and Wilson [6], Connolly et al [19] implemented a generalized DMSJ combustors model in NPSS that can identified four operation modes, including unstart, ramjet, scramjet and blowout of the combustor. Based on NPSS, they built a turbine-based combined cycle, which can operate from takeoff to above Mach 5, successfully simulating mode transition from turbomachinery to DMSJ operation.…”

Section: Introductionmentioning

confidence: 99%

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

et al. 2022

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As hypersonic vehicles are highly integrated, a multifidelity simulation method based on a commercial solver is developed to reduce simulation time for such vehicles and their propulsion systems. This method is characterized by high-level fidelity numerical analysis of external flow and low-level fidelity numerical analysis of internal flow. The external flow of a propulsion system is solved by RANS equations. The internal flow is modeled by a quasi-one-dimensional equation. The interaction between external and internal flow is governed by a CFD solver through a user-defined function (UDF). The static pressure distribution acquired from the multifidelity simulation method is in agreement with the experimental data, indicating that this simulation method can be used to study the flow physics of hypersonic propulsion systems at a reasonable cost. From a design perspective, the results indicate that the horizontal force increases with the fuel equivalence ratio, and the thrust balance is realized at φ = 0.35. The positive net thrust is maintained throughout the flight regime from Ma 4 to Ma 7, whether the combustor operates in ramjet or scramjet mode.

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Section: Introductionmentioning

confidence: 99%