A.J. Mullender, D.I.A. Poll

A two-dimensional model having a datum pressure distribution representative of that found on a typical nacelle has been tested in the 2.7m x 2.1m low turbulence, low speed, closed circuit wind tunnel at Manchester University. The model features full chord suction through a continuous laser drilled surface mounted on 13 independantly controlled plenum chambers. Boundary layer state is determined by the use of 48 microphones mounted beneath the surface and an array of hot films. Incidence is variable over the range -5° to 5° which enables a wide range of surf ace pressure distributions representative of a spectrum of designs applicable to aero-engine nacelles, from natural laminar flow (NLF) through hybrid laminar flow control (HLFC) to laminar flow control by boundary layer suction (LFC). In a parallel study, theoretical methods are being developed and validated for both the determination of the mean compressible boundary layer development with suction, using a finite difference scheme and stability analysis of the resultant boundary layer profiles. These codes will be used to determine a method for boundary layer prediction which can be applied to the design of optimised nacelles.

First European Forum on Laminar Flow Technology, Hamburg, 1992

Conference Paper

englisch

21,0 x 29,7 cm, 4 Seiten

DGLR-Bericht, 1992, 1992-06, First European Forum on Laminar Flow Technology; S.224-227; 1992; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aerodynamics, laminar flow

Bestellbar

1992