H.-P. Kreplin, G. Höhler

Future designs of laminar flow wings for transport aircrafts require mttensive wind tunnel and flight testing. Advanced measuring techniques have to be applied for these experiments. For the detection of the location of the laminar-turbulent boundary layer transition the infrared image technique is well established. Additionally, unsteady wall sensors with high temporal and spatial resolution like surf.:sce hot films and piezofoils are used to gain detailed information about the transition process in the three-dimensional boundary layers. The application of the surface hot film technique to several laminar flow investigations is described. These experiments are wind tunnel and fligh"I tests carried out within the German national program "Transonic Laminar Flow" (TLF) and within the project "European Laminar Flow Investigations" (ELFIN) of the CEC research program BRITE/EURAM.

First European Forum on Laminar Flow Technology, Hamburg, 1992

Conference Paper

englisch

21,0 x 29,7 cm, 9 Seiten

DGLR-Bericht, 1992, 1992-06, First European Forum on Laminar Flow Technology; S.123-131; 1992; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aerodynamics, boundary layer transition, flight tests, laminar flow, wind tunnel, turbulent flow

Bestellbar

1992