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LES Modeling of Scramjet Combustion
44th AIAA Aerospace Sciences Meeting and Exhibit, 2006The physics of supersonic combustion is analyzed in order to derive a new subgrid scale model for Large Eddy Simulation. Anisotropy associated to the directional Mach number typical of supersonic flows (i. e., M > 1 in only one direction) is explicitly considered by means of non-dimensionalized Navier-Stokes equations.
INGENITO, ANTONELLA +4 more
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Space Plane and Hypersonic Systems and Technology Conference, 1996
A scaling study was performed to determine the scaling laws for the performance of scramjet engines. Experiments were performed on two centrally injected scramjets in the reflected shock tunnel, T4. The scramjets had a 5:1 scale to all their dimensions. The binary scaling (pressure scaling) law was tested on the two scramjets meaning the product of the
Pulsonetti M.V., Stalker R.
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A scaling study was performed to determine the scaling laws for the performance of scramjet engines. Experiments were performed on two centrally injected scramjets in the reflected shock tunnel, T4. The scramjets had a 5:1 scale to all their dimensions. The binary scaling (pressure scaling) law was tested on the two scramjets meaning the product of the
Pulsonetti M.V., Stalker R.
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Scramjet intake and exhaust CFD studies for the HyShot scramjet flight experiment
10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference, 2001Computational fluid dynamics calculations have been performed in support of the HyShot scramjet flight experiment, which will employ two symmetrically opposed intake/combustor/exhaust nozzles (one being fuel-on, the other fuel-off). Bleed ducts for removal of intake shocks and boundary and entropy layers are incorporated.
Boyce R.R., Paull A.
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, 2020
The cooling of scramjet is a critical issue for the hypersonic vehicle, but the conventional regenerative cooling system cannot satisfy the cooling requirement and the fuel consumption for cooling will exceed the flow rate for combustion at high Mach ...
Heyang Miao, Zhongwei Wang, Yao-bin Niu
semanticscholar +1 more source
The cooling of scramjet is a critical issue for the hypersonic vehicle, but the conventional regenerative cooling system cannot satisfy the cooling requirement and the fuel consumption for cooling will exceed the flow rate for combustion at high Mach ...
Heyang Miao, Zhongwei Wang, Yao-bin Niu
semanticscholar +1 more source
2009
The renewed interest in high-speed propulsion has led to increased activity in the development of the supersonic combustion ramjet engine for hypersonic flight applications. In the hypersonic regime the scramjet engine's specific thrust exceeds that of other propulsion systems.
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The renewed interest in high-speed propulsion has led to increased activity in the development of the supersonic combustion ramjet engine for hypersonic flight applications. In the hypersonic regime the scramjet engine's specific thrust exceeds that of other propulsion systems.
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Research progress on strut-equipped supersonic combustors for scramjet application
Progress in Aerospace Sciences, 2018Scramjets are regarded as one of the most efficient air-breathing propulsion devices in supersonic flight conditions, and combustors are critical components in scramjet engines.
Jun-tao Chang +3 more
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Scramjet Experiments using Radical Farming [PDF]
, 2023 Scramjet engines are the focus of considerable interest for propulsion in the hypersonic flow regime. One of the serious technical challenges for developing scramjets is reducing the skin friction drag on the engine. The combustion chamber, in particular, is a major contributor to the skin friction drag because of the high density of the flow through ...
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A review of the scramjet experimental data base
Progress in Aerospace Sciences, 2019The frontier in hypersonic flights via an air-breathing scramjet faces a formidable challenge, because the operational principle is built on thermal compression, which is inherently interwoven with complex and delicate balancing by aerodynamics and ...
R. Seleznev, S. Surzhikov, J. Shang
semanticscholar +1 more source
Journal of Propulsion and Power, 2001
Ase ightspeedincreasesinto thehypersonicregime, stagnation pressureand temperatureinsidean airbreathing engine become so great that, for practical structures of acceptable mass, the e ow must pass through the engine at supersonic speeds so as to limit the static pressures, hence the term scramjet (supersonic combustion ramjet ).
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Ase ightspeedincreasesinto thehypersonicregime, stagnation pressureand temperatureinsidean airbreathing engine become so great that, for practical structures of acceptable mass, the e ow must pass through the engine at supersonic speeds so as to limit the static pressures, hence the term scramjet (supersonic combustion ramjet ).
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2021
The turbojet and turbofan engines discussed in detail in the previous chapters are designed for high subsonic cruise speeds. The addition of an afterburner allows the turbojet engine to operate at transonic speeds for short periods of time. As shown in Fig. 1.1, for sustained supersonic flight speeds, ramjet or scramjet engines are necessary. These are
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The turbojet and turbofan engines discussed in detail in the previous chapters are designed for high subsonic cruise speeds. The addition of an afterburner allows the turbojet engine to operate at transonic speeds for short periods of time. As shown in Fig. 1.1, for sustained supersonic flight speeds, ramjet or scramjet engines are necessary. These are
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