Revised results of the unsteady transonic pressure measurements on the LANN model

A new postprocessing procedure is applied on the data, acquired in 1981 during the unsteady transonic pressure measurements on a transport-type supercritical wing (LANN-model), oscillating in pitch. The new procedure takes the influence into account of the local boundary layer on the dynamic response of the pressure tubes. This report presents...

The international vortex flow experiment: A test case for compressible Euler codes

As part of the joint International Vortex Flow Experiment, force and pressure measurements have been carried out on a 65 deg delta wing configuration in the transonic and supersonic wind tunnels of NLR. Out of these data three test cases were selected by the organizing committee of the GAMM WORKSHOP on the "Numerical Simulation of Compressible...

2D wall interference assessment using "Calspan Pipes"

The applicability of a multi-velocity-component static pipe, proposed by CALSPAN ATC, for measuring boundary velocity vector distributions in behalf of wall interference assessment, has been explored in two-dimensional flow. Comparisons with alternative methods to derive the local flow angle from measured pipe pressures as well as analyses of...

A theoretical exploration of the capabilities of 2D flexible wall test sections for 3D testing

The applicability of two-dimensional flexible solid wall test sections for three-dimensional testing is theoretically investigated for linearized subsonic flow. The method uses known interference velocity distributions along a targer line (derived from a method of images for this particular study). From these, wall shapes are calculated that...

A system for the numerical simulation of sub- and transonic viscous attached flows around wing-body configurations

A description will be presented of a computer program system that is being used for the prediction of aircraft steady aerodynamic characteristics. Properties of the system are described from two different viewpoints. One is that of the aerodynamic designer, who needs an information system to predict lift, moment and drag characteristics and to...

The design and aerodynamic characteristics of an 18% thick shock-free airfoil (NLR 7501)

The design and experimental verification of a thick (18 %), shock free airfoil is described. The design was performed, using the NLR hodograph theory for transonic airfoil design. The airfoil was experimentally investigated in the NLR Pilot tunnel.

Influence of free-stream Mach number on transonic shock-wave boundary-layer interaction

An experiment is described in which a nominal normal shock impinges on a turbulent flat plate boundary layer. The wall pressure distribution in the interaction region was measured for Mach numbers in front of the shock of 1.40, 1.44 and 1.46. The Reynolds number based on shock position was 18 X 10(6) and based on momentum thickness at the start...

Investigations of the transonic flow around oscillating airfoils

Exploratory wind-tunnel experiments in high-subsonic and transonic flow on a conventional airfoil with oscillating flap and a supercritical airfoil oscillating in pitch are described. In the analysis of the experimental results, emphasis is placed upon the typical aspects of transonic flow, namely the interaction between the steady and unsteady...