This report documents the results of a study to address the long range, strategic planning required by NASA's Revolutionary Computational Aerosciences (RCA) program in the area of computational fluid dynamics (CFD), including future software and hardware requirements for High Performance Computing (HPC). Specifically, the "Vision 2030" CFD study is to provide a knowledge-based forecast of the future computational capabilities required for turbulent, transitional, and reacting flow simulations across a broad Mach number regime, and to lay the foundation for the development of a future framework and/or environment where physics-based, accurate predictions of complex turbulent flows, including flow separation, can be accomplished routinely and efficiently in cooperation with other physics-based simulations to enable multi-physics analysis and design. Specific technical requirements from the aerospace industrial and scientific communities were obtained to determine critical capability gaps, anticipated technical challenges, and impediments to achieving the target CFD capability in 2030. A preliminary development plan and roadmap were created to help focus investments in technology development to help achieve the CFD vision in 2030.

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CFD Vision 2030 Study: A Path to Revolutionary Computational Aerosciences

A comprehensive research program designed to investigate the ability of computational methods to predict
stability and control characteristics of a generic unmanned combat air vehicle has been undertaken. The integrated
approach to simulating static and dynamic stability characteristics was performed by the NATO Research and
Technology Organization Task Group AVT-161. The vehicle named Stability and Control CONfiguration
(SACCON) was the subject of an intensive computational and experimental study. The stability characteristics of the
vehicle were evaluated via a highly integrated approach, where computational fluid dynamics and experimental
results were used in a parallel and collaborative fashion. The results show that computational methods have made
great strides in predicting static and dynamic stability characteristics, but several key issues need to be resolved
before efficient, affordable, and reliable predictions are available.

Integrated Computational/Experimental Approach to Unmanned Combat Air Vehicle Stability and Control Estimation

A comprehensive research program designed to investigate the ability of computational methods to predict stability and control characteristics of realistic flight vehicles has been undertaken. The integrated approach to simulating static and dynamic stability characteristics for a generic UCAV and the X-31 configuration was performed by NATO RTO Task Group AVT-161. The UCAV, named SACCON (Stability and Control Configuration), and the X-31 are the subject of an intensive computational and experimental study. The stability characteristics of the vehicles are being evaluated via a highly integrated approach, where CFD and experimental results are being used in a parallel and collaborative fashion. The results show that computational methods have made great strides in predicting static and dynamic stability charactersitics, but several key issues need to be resolved before efficient, affordable, and reliable predictions are available.

An Integrated Computational/Experimental Approach to UCAV Stability & Control Estimation: Overview of NATO RTO AVT-161

Within the NATO Research and Technology Organisation Applied Vehicle Technology (AVT)-161 task group,
titled “Assessment of Stability and Control Predictions for NATO Air and Sea Vehicles,” a 53 swept and twisted
lambda wing with rounded leading edges is considered. In a first step, the symmetric flow conditions are analyzed in
this paper in order to understand the corresponding flow physics. Experiments by the task group are used to develop
proper numerical simulation tools for further applications in the design process of unmanned combat aerial vehicles
as a part of future air-combat systems. The philosophy of the configuration under consideration is explained. The
vortical flowfield is simulated using the DLR, German Aerospace Center TAU-Code applied with different
turbulence models on various computational grids. Finally, a best practice is evaluated for medium and large angles
of attack. A combination of these numerical results and experimental data lead to a proper understanding of the
complex flow structure. Furthermore, this paper addresses the necessity for the predictability and understanding of
controlled and uncontrolled flow separation, together with the interaction of the corresponding vortex systems in
order to estimate stability and control issues for the entire flight envelope.

Flow Physics Analyses of a Generic Unmanned Combat Aerial Vehicle Configuration

In this paper, mesh deformation based on radial basis function (RBF) interpolation is applied to the deflection of aircraft control surfaces. A confinement technique is presented, which locally restricts mesh deformation to the vicinity of the moving component and leaves the surfaces of other components unaffected. This technique is shown to have the potential to significantly reduce the CPU time necessary for evaluating the RBF interpolants. Motivated by the directionality of control surface deflection, the idea of treating each direction of the displacements separately is introduced. It is employed for the adaptive selection of centers, and the approach termed sequential uni-variate center adaptation. It is shown to be more efficient for both solution and evaluation processes than the standard approach, in which the same set of centers is used for every direction. Furthermore, different data sites may be imposed for different directions. It is demonstrated that this enables sliding motion of the elements on the face of a mesh block. Thereby, large control surface deflections are possible, despite the presence of a small spanwise gap between control surface and parent component. These techniques are successfully applied to the deflection
of aileron and horizontal tail of a generic fighter aircraft configuration.

Aircraft control surface deflection using RBF-based mesh deformation

Selected results of the DLR Project SikMa-"Simulation of Complex Maneuvers" are presented. The objective of the SikMa Project is to develop and validate a numerical tool to simulate the unsteady aerodynamics of a free flying aeroelastic combat aircraft, by use of coupled aerodynamic, flight mechanics and aeroelastic computations. To achieve this objective, the unstructured, time-accurate flow-solver TAU is coupled with a computational module solving the flight mechanics equations of motion and a structural mechanics code determining the structural deformations. The numerical results are validated by experimental data. For this purpose several specific wind tunnel experiments with different wind tunnel models are carried out.

/pdf/numerical-simulation-of-maneuvering-aircraft-by-aerodynamic-1teff3a1xi.pdf

Numerical Simulation of Maneuvering Aircraft by Aerodynamic, Flight Mechanics and Structural Mechanics Coupling

/pdf/numerical-simulation-of-maneuvering-aircraft-by-aerodynamic-2nk7cvo2y8.pdf

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Numerical Simulation of Maneuvering Aircraft by Aerodynamic, Flight Mechanics and Structural Mechanics Coupling

Numerical Simulation of Maneuvering Aircraft by Aerodynamic, Flight Mechanics and Structural Mechanics Coupling