Scramjet Engine Model MASIV: Role of Mixing, Chemistry and Wave Interaction

Abstract

This paper provides details of the combustion and inlet submodels used in the Michigan-Air Force Scramjet In Vehicle (MASIV) model. The model solves conservation equations in 1-D, using several modeling techniques to retain some of the fidelity of higher-order simulations. Inlet wave interactions, fuel mixing and finite-rate chemistry are considered. The order of the problem is reduced by physics-based, experimentally-verified algebraic scaling laws, which retains the required physics but reduces the computation time of the problem to seconds, instead of the several days required by computational fluid dynamics (CFD). Scaling coefficients and assumptions are given. The model is used to compute the performance of an experimental configuration for which real

Reduced-Order Modeling of Turbulent Reacting Flows with Application to Ramjets and Scramjets

“…A tool that can solve these configurations in a short time to acceptable accuracy is highly desirable for control and design applications, such as control evaluation, and multidisciplinary optimization (MDO). The proposed one-dimensional method [6][7][8][9][10] solves for the heat release distribution for both subsonic and supersonic internal flows.…”

An aircraft-propulsion geometry/performance collaborative design method

“…Various authors [13][14][15][16] documented the quasi-one dimensional combustor flow field with particular emphasizes. Real-time combustor performance simulation was taken as the main requirement in this paper and a list of model simplifications and implementations were fulfilled in the combustor model: (1) Chemical reactions were narrowed down to a single Hydrogen reactive process [14]; (2) Molar weight was supposed to be constant alongside the flow stream for mean molar weight was hardly changing for hydrogen fueled situation; (3) One dimensional grid was discretized to be coarse enough for enabling the fast calculation; (4) Turbulence mixing model was simplified to be linear function of injector length; (5) Cantera package [28] was experienced to be convenient for combining into the MATLAB development environment.…”

“…M. Smart [7,8] demonstrated an isolator-combustor integrated modeling procedures and predicted the isolator variation and thermal choke behaviors. S. Torrez et al [13], C. Birzer et al [14], N. Gupta [15] and K. Tran [16] structured various scramjet models with different purposes: accelerated (not real-time) detailed scramjet performance observation, simulation based simplified scramjet model, scalable modular scramjet models and user accessible open source scramjet analysis code respectively. H. Sobieczky et al [17][18][19] developed osculating plane based streamline tracing method for constructing the lower surface of hypersonic vehicles and waveriders, which enables fast wingbody generation and validation procedures.…”

Surrogate modeling of a 3D scramjet-powered hypersonic vehicle based on screening method IFFD

“…[1][2][3] The main challenging issues include: aerodynamic characteristics, 4,5 scramjet-powered propulsion system, [6][7][8] and aeroelastic characteristics. 10,11 Several programs have been developed for integrated design, analysis, and optimization of hypersonic vehicles, such as the Aerospace Vehicles Simulation and Analysis Program for Hypersonics (ASAP-Hypersonics), 12 the Integrated Design & Engineering Analysis (IDEA), 13 the HOLIST, 14 the Michigan-Air Force Scramjet In Vehicle (MASIV) 8 and so on. With the advance of modern aerospace systems, the major challenges have come to the formulation of the efficient high-fidelity model for engineering full-scale analysis and optimization.…”