The potential positive effects of ground proximity on the aerodynamic performance of a \Ving or aerofoil have long been established, but at transonic speeds the fonnation of shock waves betvveen the body and the ground plane would have significant consequences. A numerical study of the aerodynamics of an lu\E2822 aerofoil section in ground eiiect flight was conducted at freestream Mach numbers ...

A large-scale, real-world application of Evolutionary Multi-Objective Optimization is reported. The Multidisciplinary Design Optimization among aerodynamics, structures, and aeroelasticity of the wing of a transonic regional jet aircraft was performed using highfidelity evaluation models. Euler and Navier-Stokes solvers were employed for aerodynamic evaluation. The commercial software NASTRAN w...

This article deals with the numerical solution of compressible turbulent flows in aerodynamics. Compressible turbulent flow is described by the system of Favre averaged Navier-Stokes equations, which are closed by the explicit algebraic Reynolds stress model (EARSM) of Wallin and Johansson. The averaged Navier-Stokes equations together with EARSM model of turbulence are discretized by the finit...

In the German Aerospace Center, DLR, an internal project has been launched to investigate different UCAV configurations. One aspect, covered by the Institute of Aeroelasticity and the Institute of Aerodynamics and Flow Technology, is the wind tunnel test of a UCAV wing in subsonic and transonic flow. The model shall show measurable static aeroelastic deformations. Main goals of the tests will b...

It is not easy for the system identification-based reduced-order model ROM and even eigenmode based reduced-order model to predict the limit cycle oscillation generated by the nonlinear unsteady aerodynamics. Most of these traditional ROMs are sensitive to the flow parameter variation. In order to deal with this problem, a support vector machineSVMbased ROM was investigated and the general cons...

How to determine accurately and efficiently the aerodynamic forces of aircraft in high-speed flow is one great challenges modern aerodynamics. In this Letter we propose a new similarity law for steady transonic-supersonic over thin bodies. The based on local Mach number frozen principle. It depends both specific heat ratio free-stream number. enables lift drag coefficients from that reference s...

By using a combined analytical–computational methodology, a unified modelling of aerodynamic indicial functions covering the incompressible, subsonic compressible, transonic, and supersonic flight speed regimes is presented. The procedure is carried out in conjunction with a computational fluid dynamic analysis. For a plunging–pitching airfoil, selected unsteady aerodynamic load expressions hav...

An integrated design of a robust fault detection filter and control system for a re-entry vehicle is presented. The integrated architecture is based on the four-block Youla parametrization which allows to better and directly trade-off filter and control design objectives in the face of disturbances and uncertainties. H∞-optimization techniques are used to design the integrated controller/filter...

Fluid–structure interaction problems in general are often too complex to solve analytically and so they have to be analyzed by means of experiments or numerical simulation. Studying these phenomena requires modeling of both fluid and structure. Many approaches in computational aero elasticity seek to synthesize independent computational approaches for the aerodynamic and the structural dynamic ...