Demonstration of an automated CFD system for three-dimensional flow simulations

In this paper the capabilities of an automated CFD system which is currently available at NLR are demonstrated. Transonic flow around the AS28G wing/body configuration and hypersonic flow through a generic three-dimensional mixed-compression airbreathing inlet are simulated. An assessment of the level of automation of the current CFD-system is...

Structured parallelization of a multi-block Navier-Stokes solver targeting distributed memory platforms

SOLEQS is a sequential three-dimensional multi-block multi-zone compressible Navier-Stokes solver, produced by NLR. In this paper is described how this large-scale application code in the order of 120,000 lines can be parallelized towards different computing platforms in a structured and manageable way. This paralellization is done step-wise,...

Boundary-layer calculations on the leeward surface of a slender delta wing at incidence

The three dimensional flow field around delta wings with leading-edge vortex flow can be computed with panel methods. However, secondary flow separation may occur on the leeward surface of the wing. The associated free vortex sheet can be modeled in the potential flow calculation method, if the location of the secondary separation is provided by...

Three-dimensional flight-path reconstruction by means of spline approximation

In NLR TR 82075 U, a method has been developed to reconstruct the flight-path of a symmetric flight, by representing this path by a set of splines. In the present report, the same method is being applied to a three-dimensional flight over a rotating earth. Preliminary results are comparable in accuracy and computing time to the Kalman (Square...

Application of model following control and estimation techniques to attitude control of manoeuvring spacecraft Part II: Simulation software description

This document describes two computer programs developed during a study of the application of modern control techniques in the area of spacecraft attitude control. Theory and simulation results are described in part I of this report. In part II a general overview of the tasks of the simulation program is presented, and program design aspects are...

Aspects of second- and third-order panel methods demonstrated for the two-dimensional flat plate problem

Characteristics of three second-order and two third-order panel method formulations for the incompressible flow about a flat plate at incidence are investigated. The second order methods employ quadratic representations for the doublet distribution, either based on quadratic B-splines or on a combination of a Taylor series expansion and finite...

A finite difference method for the calculation of transonic flow about a wing, based on a small perturbation theory

A calculation method, based upon transonic small perturbation theory, is presented for the transonic flow about a semi-wing. The influence of a body can be simulated by prescribing appropriate transverse velocities in a vertical plane through the wing root. Due to the small perturbation assumption the wing should be thin and have little dihedral...