* Note that appearance on this list does not guarantee that the
abstract has been or will be accepted. All submitted abstracts
will be reviewed for suitability and technical content.
Acceptance will be confirmed via email with the submitting author.
Aircraft and UAS Design & Applications
Abstract ID: 50DCASS-002
Multi-Fidelity Aerostructural Optimization of ESAV including Flutter Constraints
Markus Rumpfkeil
University of Dayton
Phil Beran
Air Force Research Laboratory
The traditional design process relies heavily upon low-fidelity models for time and cost savings. However, the reduced accuracy of low-fidelity tools can often lead to the discovery of inadequacies late in the design process. These deficiencies can result either in costly redesigns or the acceptance of worse-than-advertised performances. Multi-fidelity methods attempt to blend the reduced cost of low-fidelity models with the increased accuracy and reliability of high-fidelity ones. In this presentation, a gradient-based multi-fidelity constrained optimization approach is applied to an aeroelastic drag minimization of an efficient supersonic air vehicle (ESAV). The highest and lowest fidelity levels considered are Euler and panel solutions, respectively, all combined with a modal structural solver. Imposed constraints are for lift, and pitching moments as well as flutter suppression. The results show that a drag reduction is possible while satisfying all constraints and that a developed multi-fidelity optimizer performs better than a purely high-fidelity one.
Abstract ID: 50DCASS-003
Development of a High-Speed Vehicle Conceptual Design Process using ADAPT Framework
Samuel Atchison
AFIT Contractor
Matthew Madayag and Jose Camberos
Air Force Institute of Technology
The significant multidisciplinary challenges of high-speed vehicle design and development make the design process for these vehicles more complex and integrated than that of traditional aircraft. Along with this integration, the higher speeds invite more physics that the selected analysis tools must capture for accurate analysis and evaluation. To meet this need, design frameworks allow the integration of analysis tools at selected (and variable) fidelity levels. One such design tool built specifically for aircraft design is the Aircraft Design, Analysis, Performance, and Tradespace (ADAPT) framework. This study describes the implementation of a design process for high-speed vehicles through the initial integration of the Engineering Sketch Pad (ESP), Configuration-Based Aerodynamics (CBAero), and Automatic Structural Layout Tool (AutoSaLT) as plugins within the ADAPT framework. We discuss the integration process of these tools in detail to show how we developed the plugins and linked them in ADAPT's workflow. We then show geometric, material, and structural layout trade studies on a selected geometry to showcase the capabilities of ADAPT, the potential of developing a design process within this framework, and to provide some insights from the trade study results. Distribution Statement A: Approved for Public Release; Distribution Unlimited. Public Release # 88ABW-2024-0904
Data Analysis & Uncertainty Quantification
Abstract ID: 50DCASS-004
Uncertainty Propagation in Transient Heat Transfer from an Extended Surface
Rama Gorla
Air Force Institute of Technology
Edwin Forster
Air Force Research Laboratory
Awaiting public release.
Fluid Dynamics
Abstract ID: 50DCASS-001
Numerical Simulation of Circulation Control For a Wing Section Using a Coanda Jet
Donald Rizzetta
Air Force Research Laboratory
Daniel Garmann
Air Force Research Laboratory
Large-eddy simulations were carried out to describe the subsonic ow over a wing section, using Coanda-jet circulation control to augment lift. The section geometry consists of a modified supercritical airfoil, with a jet that is blown over a one quarter circular cylindrical trailing-edge Coanda surface. Because the configuration does not include a slotted trailing-edge flap, the mechanical complexity and weight may be reduced. The computations correspond to an experimental investigation, that provides data for comparison. High-fidelity solutions were obtained to the unsteady three-dimensional Navier-Stokes equations, at a chord-based Reynolds of 475,000 and freestream Mach number of 0.1. Several angles of attack were considered, and solutions were obtained both with and without circulation control. In the control cases, three different jet-mass flow rates were simulated at each angle of attack. A grid-resolution study was carried out to assure numerical accuracy. Comparisons are made between the respective cases and with the experimental data, and features of the flowfields are characterized. It was found that Coanda-jet control was able to augment lift in excess of factors of three with reasonable amounts of jet-mass flow.
Heat Transfer & Thermal Management
Abstract ID: 50DCASS-005
Investigation of the Operating Mechanism of the Ranque-Hilsch Vortex Tube
James Rutledge
Air Force Institute of Technology
Matthew N. Fuqua
Air Force Life Cycle Management Center
Awaiting public release.
