Results 61 to 70 of about 4,282 (226)
Numerical Investigation on the Effect of Fuel‐Rich Degree in the RBCC Engine under the Ejector Mode
International Journal of Aerospace Engineering, Volume 2024, Issue 1, 2024.The ejector mode of the Rocket‐Based Combined‐Cycle (RBCC) engine is characterized by high fuel consumption. This study is aimed at investigating the influence of the rocket fuel‐rich degree on the RBCC engine’s performance under the ejector mode combined with simultaneous mixing and combustion (SMC).
Yizhi Yao +10 more
wiley +1 more source
Influence of Geometric Parameters on Intake Performance of 3D Ramp‐Type Scramjet Inlet
International Journal of Aerospace Engineering, Volume 2024, Issue 1, 2024.The methods based on the assumption of inviscid flow are typically used for the initial design of the scramjet inlet geometry, but the presence of a viscous boundary layer can degrade the validity of the results and lead to nonoptimal operation. This study explored the design space of three‐dimensional ramp‐type scramjet inlet geometry and investigated
Sunoh Kang +3 more
wiley +1 more source
Modeling of Supersonic Combustion Systems for Sustained Hypersonic Flight
Energies, 2017 Through Computational Fluid Dynamics and validation, an optimal scramjet combustor has been designed based on twin-strut Hydrogen injection to sustain flight at a desired speed of Mach 8.
Stephen M. Neill, Apostolos Pesyridis
doaj +1 more source
Operating characteristics of the Langley Mach 7 Scramjet Test Facility [PDF]
Operating characteristics of the Langley Mach 7 Scramjet Test Facility are described. The facility is designed for testing airframe integrated scramjet (supersonic combustion ramjet) engine models.
Guy, R. W. +3 more
core +1 more source
Langley Mach 4 scramjet test facility [PDF]
An engine test facility was constructed at the NASA Langley Research Center in support of a supersonic combustion ramjet (scramjet) technology development program.
Anderson, G. Y. +4 more
core +1 more source
Case Studies in Thermal Engineering, 2019 The standard k- ε turbulence model, two dimensional NavierStokes equations along with eddy-dissipation/finite-rate reaction model has been applied to analyze the flow dynamics of the scramjet combustor with the cold-flow and ignited engine conditions. In
S.K. Gugulothu, Prabhu Kishore Nutakki
doaj +1 more source
Hypersonic Airbreathing Missile [PDF]
A hypersonic airbreathing missile using dual mode scramjet engines for propulsion is described. The fuselage is constructed of a material with a high heat sink capacity and is covered with a thermal protective shield and lined with an internal insulating
Hunt, J. L. +2 more
core +1 more source
Hypersonic cruise aircraft propulsion integration study, volume 1 [PDF]
A hypersonic cruise transport conceptual design is described. The integration of the subsonic, supersonic, and hypersonic propulsion systems with the aerodynamic design of the airframe is emphasized.
Brewer, G. D., Morris, R. E.
core +1 more source
Thermal design and analysis of a hydrogen-burning wind tunnel model of an airframe-integrated scramjet [PDF]
An aerodynamic model of a hydrogen burning, airframe integrated scramjet engine has been designed, fabricated, and instrumented. This model is to be tested in an electric arc heated wind tunnel at an altitude of 35.39 km (116,094 ft.) but with an inlet ...
Guy, R. W. +3 more
core +1 more source
Airframe-integrated propulsion system for hypersonic cruise vehicles [PDF]
Research on a new, hydrogen burning, airbreathing engine concept which offers good potential for efficient hypersonic cruise vehicles is considered. Features of the engine which lead to good performance include; extensive engine-airframe integration ...
Huber, P. W., Jones, R. A.
core +1 more source