Computational Fluid Dynamics Prediction of Hyper-X Stage Separation Aerodynamics

Buning, Pieter G.; Wong, Tin-Chee; Dilley, Arthur D.; Pao, J. L.

doi:10.2514/2.3771

Cited by 30 publications

(22 citation statements)

References 12 publications

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“…A perfect gas with constant specific heat ( p C ) of 2433 J/(kgK) and constant specific heat ratio (  ) of 1.14 is assumed, which is adequate for the simulation (Wang, 1997;Buning et al, 2001 and. The conservation equations of mass, momentum and energy are expressed in tensor form as…”

Section: Flow Field Governing Equationsmentioning

confidence: 99%

Intermittent Gas Resonance in Stage Separation Flow Field of Multistage Rocket

Gao¹,

Fu²

2012

Engineering Applications of Computational Fluid Mechanics

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ABSTRACT:The aerodynamic-dynamic coupled simulation was performed to investigate the interstage flow characteristics of a multistage rocket in the course of stage separation. Results show that the stage separation exhibits five phases, i.e., the initial transient phase, the smooth gas leakage phase, the gas resonance phase, the suspension phase of gas resonance and the resumed gas resonance phase. There is a striking contrast between stage separation flow of a rocket and that of a gas resonance tube, which shows iso-magnitude and iso-period oscillation. The present analysis shows that shock wave structures of the interstage and relative distance between the two stages are the main conditions which lead to this interesting phenomenon.

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Section: Flow Field Governing Equationsmentioning

confidence: 99%

Intermittent Gas Resonance in Stage Separation Flow Field of Multistage Rocket

Gao¹,

Fu²

2012

Engineering Applications of Computational Fluid Mechanics

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“…With continual advances in computing power, computational fluid dynamic (CFD) tools have now become viable to confirm and extend experimental studies in the area of separation aerodynamics. 13 The work described herein represents a new level of coordination of both existing and new experimental, CFD, and engineering methods to develop a suite of synergistic tools to analyze aerodynamic separation issues from transonic to hypersonic conditions.…”

Section: Previous Workmentioning

confidence: 99%

Overview of Transonic to Hypersonic Stage Separation Tool Development for Multi-Stage-To-Orbit Concepts

Murphy

Buning

Pamadi

et al. 2004

24th AIAA Aerodynamic Measurement Technology and Ground Testing Conference

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An overview of research efforts at NASA in support of the stage separation and ascent aerothermodynamics research program is presented. The objective of this work is to develop a synergistic suite of experimental, computational, and engineering tools and methods to apply to vehicle separation across the transonic to hypersonic speed regimes. Proximity testing of a generic bimese wing-body configuration is on-going in the transonic (Mach numbers 0.6, 1.05, and 1.1), supersonic (Mach numbers 2.3, 3.0, and 4.5) and hypersonic (Mach numbers 6 and 10) speed regimes in four wind tunnel facilities at the NASA Langley Research Center. An overset grid, Navier-Stokes flow solver has been enhanced and demonstrated on a matrix of proximity cases and on a dynamic separation simulation of the bimese configuration. Steady-state predictions with this solver were in excellent agreement with wind tunnel data at Mach 3 as were predictions via a Cartesian-grid Euler solver. Experimental and computational data have been used to evaluate multi-body enhancements to the widely-used Aerodynamic Preliminary Analysis System, an engineering methodology, and to develop a new software package, "SepSim," for the simulation and visualization of vehicle motions in a stage separation scenario. Web-based software will be used for archiving information generated from this research program into a database accessible to the user community. Thus, a framework has been established to study stage separation problems using coordinated experimental, computational, and engineering tools.

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“…With continual advances in computing power, computational fluid dynamic (CFD) tools have now become viable to confirm and extend experimental studies in the area of separation aerodynamics. 14 The stage separation tool development program, of which the work described in this paper is a part, represents a new level of coordination of both existing and new experimental, CFD, and engineering methods to develop a suite of synergistic tools to analyze aerodynamic separation issues from transonic to hypersonic conditions.…”

Section: Previous Workmentioning

confidence: 99%

Experimental Stage Separation Tool Development in NASA Langley's Aerothermodynamics Laboratory

Murphy

Scallion

2005

AIAA Atmospheric Flight Mechanics Conference and Exhibit

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As part of the research effort at NASA in support of the stage separation and ascent aerothermodynamics research program, proximity testing of a generic bimese wing-body configuration was conducted in NASA Langley's Aerothermodynamics Laboratory in the 20-Inch Mach 6 Air Tunnel. The objective of this work is the development of experimental tools and testing methodologies to apply to hypersonic stage separation problems for future multi-stage launch vehicle systems. Aerodynamic force and moment proximity data were generated at a nominal Mach number of 6 over a small range of angles of attack. The generic bimese configuration was tested in a belly-to-belly and back-to-belly orientation at 86 relative proximity locations. Over 800 aerodynamic proximity data points were taken to serve as a database for code validation. Longitudinal aerodynamic data generated in this test program show very good agreement with viscous computational predictions. Thus a framework has been established to study separation problems in the hypersonic regime using coordinated experimental and computational tools.

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Computational Fluid Dynamics Prediction of Hyper-X Stage Separation Aerodynamics

Cited by 30 publications

References 12 publications

Intermittent Gas Resonance in Stage Separation Flow Field of Multistage Rocket

Intermittent Gas Resonance in Stage Separation Flow Field of Multistage Rocket

Overview of Transonic to Hypersonic Stage Separation Tool Development for Multi-Stage-To-Orbit Concepts

Experimental Stage Separation Tool Development in NASA Langley's Aerothermodynamics Laboratory

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