Direct Numerical Simulation of Film Cooling in Hypersonic Boundary-Layer Flow

J. Linn () and M. J. Kloker ()
Additional contact information
J. Linn: Universität Stuttgart, Institut für Aerodynamik und Gasdynamik
M. J. Kloker: Universität Stuttgart, Institut für Aerodynamik und Gasdynamik

A chapter in High Performance Computing in Science and Engineering '08, 2009, pp 171-189 from Springer

Abstract: Summary Effusion cooling by discrete slits and holes in various laminar zero-pressure gradient super- and hypersonic boundary layers is investigated using direct numerical simulation. For an adiabatic Mach-6 boundary layer it was found that slits are better than holes due to the lower blowing velocity. Slit blowing causes a destabilisation of 2 nd -mode disturbances, and a complete stabilisation of 1 st modes despite the generated maxima of the spanwise vorticity inside the boundary layer. Hole blowing gives rise to counter-rotating streamwise vortices, with a noticeable laminar-flow destabilisation only for large spanwise hole spacings. Computational aspects such as the performance of the numerical code on the supercomputer NEC SX-8 and optimization of the code are also discussed.

Date: 2009
References: Add references at CitEc
Citations:

There are no downloads for this item, see the EconPapers FAQ for hints about obtaining it.

Related works:
This item may be available elsewhere in EconPapers: Search for items with the same title.

Export reference: BibTeX RIS (EndNote, ProCite, RefMan) HTML/Text

Persistent link: https://EconPapers.repec.org/RePEc:spr:sprchp:978-3-540-88303-6_13

Ordering information: This item can be ordered from
http://www.springer.com/9783540883036

DOI: 10.1007/978-3-540-88303-6_13

Access Statistics for this chapter

More chapters in Springer Books from Springer
Bibliographic data for series maintained by Sonal Shukla () and Springer Nature Abstracting and Indexing ().