Summary
An experiment at high subsonic speeds on a two-dimensional aerofoil model is described, with a passive system for the control of shock waves via a porous skin and under-surface cavity. Passive control utilises the pressure gradient across the shock wave to induce a secondary flow through the surface and underlying cavity, causing injection into and suction from the boundary layer upstream and downstream of the shock wave, respectively. The displacement surface so formed induces compression waves which weaken the main shock wave, thereby reducing wave drag.
The measurements show that while passive control apparently reduces wave drag it also significantly increases viscous drag, consequently increasing drag overall.
This is a preview of subscription content, log in via an institution to check access.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
Preview
Unable to display preview. Download preview PDF.
Similar content being viewed by others
References
“Boundary layer and flow control” Lachmann G V, Pergammon Press, 1961.
“Control of flow separation” Chang P, Pergammon Press, 1972.
“Shock wave/turbulent boundary-layer interaction and its control” Délery J M, Progress in Aerospace Sciences, 22 pp 209–280, 1985.
“Transonic shock-boundary layer control” Krogmann P and Stanewsky E, Proceedings of the 14th Congress of ICAS, Toulouse, France, Paper No. 84-2. 3. 2. September 1984.
“Improvement of transonic airfoil performance through passive shock/boundary-layer interaction control” Thiede P and Krogmann P, IUTAM Symposium, Palaiseau, France, 1985, Ed J. Délery, Springer, Berlin, 1986.
“ONERA activities on drag reduction” Thibert J J, Reneaux J and Schmitt V, Proceedings of the 17th Congress of ICAS, Stockholm, Sweden, Paper No. 90-3. 6. 1, September 1990.
“The aerodynamic performance of laser drilled sheets” Poll D I A, Danks M and Humphreys B E, paper presented to First European Symposium on Laminar Flow, Hamburg, Germany, March 1992.
“Determination of profile drag at high speeds by pitot traverse methods” Lock C N H, Hilton W F and Goldstein S, ARC R&M 1970, 1940.
“An improved semi-inverse version of the viscous Garabedian and Korn method” Ashill P R, Wood R F and Weeks D J, RAE Technical Report TR 87002, 1987.
“Calculation and measurement of transonic flows over aerofoils with novel rear sections” Ashill P R, Proceedings of the 16th Congress of ICAS, Jerusalem, Israel, Paper No. 88-3. 10. 2. September 1988.
“Passive control of a shock wave/turbulent boundary layer interaction in a transonic flow” Bur R, Rech Aérosp. No 1992-6 pp l1–30, 1992.
Author information
Authors and Affiliations
Editor information
Rights and permissions
Copyright information
© 1997 Friedr. Vieweg & Sohn Verlagsgesellschaft mbH, Braunschweig/Wiesbaden
About this chapter
Cite this chapter
Fulker, J.L., Simmons, M.J. (1997). An Experimental Investigation of Passive Shock/Boundary-Layer Control on an Aerofoil. In: Stanewsky, E., Délery, J., Fulker, J., Geißler, W. (eds) EUROSHOCK - Drag Reduction by Passive Shock Control. Notes on Numerical Fluid Mechanics (NNFM), vol 56. Vieweg+Teubner Verlag. https://doi.org/10.1007/978-3-322-90711-0_22
Download citation
DOI: https://doi.org/10.1007/978-3-322-90711-0_22
Publisher Name: Vieweg+Teubner Verlag
Print ISBN: 978-3-322-90713-4
Online ISBN: 978-3-322-90711-0
eBook Packages: Springer Book Archive