CFD Approaches for Simulation of Wing-Body Stage Separation

Buning, Pieter G.; Gomez, Reynaldo J.; Scallion, W. I.

doi:10.2514/6.2004-4838

Cited by 66 publications

(22 citation statements)

References 19 publications

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“…Computational Codes: In a companion computational tool development program for wing-body stage separation 3 , a significant effort has been expended on merging two existing versions of the OVERFLOW NavierStokes flow solver. The resulting code is referred to as OVERFLOW 2, and includes the capabilities and features of OVERFLOW-D and OVERFLOW Version 1.8, enabling a fully-viscous, 6-degree-of-freedom, multi-body simulation capability.…”

Section: Methodsmentioning

confidence: 99%

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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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Section: Methodsmentioning

confidence: 99%

“…3 Experimental data obtained in the LAL serves as a valuable means of validation for these computational tools.…”

Section: Objectivesmentioning

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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“…A similar paradigm is implemented in OVERFLOW and has achieved notable success. 17,18 One key difference between Helios and OVERFLOW is the latter uses a near-body grid system composed of structured curvilinear grids. Also, Helios's implementation couples disparate solvers whereas OVERFLOW's near-body solver, domain connectivity, and offbody Cartesian solver are all within the same code.…”

Section: Computational Infrastructurementioning

confidence: 99%

Automated Off-Body Cartesian Mesh Adaption for Rotorcraft Simulations

Kamkar

Jameson

Wissink³

et al. 2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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A new adaptive mesh refinement strategy is presented that couples feature-detection with local error-estimation. The goal is to guide refinement to key vortical features using feature detection, and to terminate refinement when a maximum acceptable error level has been reached. The feature detection scheme, which has been presented in previous related work, uses a special local normalization that allows it to properly identify regions of high vortical strength without tuning to a particular vorticity value. The newly introduced error estimation scheme applies a Richardson extrapolation-like procedure to detect local truncation error based on solutions from different grid levels. The error is then used the computed error to determine when to cut off further refinement. The paper presents a theoretical analysis of the scheme, applying it to computations of an isolated vortex and comparing to an exact solution. The scheme is implemented as part of the off-body Cartesian solver in the Helios code. Two practical cases are considered, resolution of the wake tip vortex from a NACA 0015 wing, and resolution of the wake structure of a quarter-scale V22 rotorcraft.

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“…Evaluation of static (basic) coefficient data (refer equation (14)) was performed employing Computational Fluid Dynamics (CFD) [7,13] technique. All the parameters were obtained as a function of control effort, angle of attack (D ), side slip ( E ) and mach number (M).…”

Section: Aerodynamic Parameters Estimationmentioning

confidence: 99%

Dynamic Modeling & Stability Analysis of a Generic UAV in Glide Phase

2017

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Abstract. In this paper, we present dynamic modelling and stability analysis of a generic UAV in the glide phase under engine failure condition. When such extreme phenomena occurs, the most desirable requirement is to survive that stage by keeping the vehicle controllable by maintaining its orientation and to glide the vehicle towards the intended direction with maximum extended range. This study investigates the stability aspects of one such aerial vehicle under engine failure condition. In the proposed architecture, a six degree of freedom vehicle dynamic simulation model is implemented through a set of coupled non-linear differential equations. The aerodynamic forces and moments encountered by the UAV during various phases of the flight are ascertained through empirical / non-empirical techniques. Nonlinear constrained optimization technique is employed to evaluate the steady state values of the optimized trajectory for the complete flight regime. Results from dynamical systems theory are applied to investigate local stability characteristics of UAV around the steady state. Complete set of dynamic modes of UAV throughout the glide phase are evaluated and mode content in each of the motion variable is determined using modal decomposition technique. The dynamic characteristics of the open-loop configuration are assessed to generate adequate benchmark performance for closed-loop controller design

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CFD Approaches for Simulation of Wing-Body Stage Separation

Cited by 66 publications

References 19 publications

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

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

Automated Off-Body Cartesian Mesh Adaption for Rotorcraft Simulations

Dynamic Modeling & Stability Analysis of a Generic UAV in Glide Phase

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