Wp-1 reference cases of laminar and turbulent interactions

Jean Paul Dussauge*, Reynald Bur, Todd Davidson, Holger Babinsky, Matteo Bernardini, Rogier Giepman, Ferry Schrijer, Bas van Oudheusden, Andrey Sidorenko, More Authors

*Corresponding author for this work

Research output: Chapter in Book/Conference proceedings/Edited volumeChapterScientificpeer-review

25 Downloads (Pure)


In order to be able to judge the effectiveness of transition induction in WP-2, reference flow cases were planned in WP-1. There are two obvious reference cases—a fully laminar interaction and a fully turbulent interaction. Here it should be explained that the terms “laminar” and “turbulent” interaction refer to the boundary layer state at the beginning of interaction only. There are two basic configurations of shock wave boundary layer interaction and these are a part of the TFAST project. One is the normal shock wave, which typically appears at the transonic wing and on the turbine cascade. The characteristic incipient separation Mach number range is about M = 1.2 in the case of a laminar boundary layer and about M = 1.32 in the case of turbulent boundary layer. The second typical flow case is the oblique shock wave reflection. The most characteristic case in European research is connected to the 6th FP IP HISAC project concerning a supersonic business jet. The design speed of this airplane is M = 1.6. Therefore the TFAST consortium decided to use this Mach number as the basic case. Pressure disturbance at this Mach number is not very high and can be compared to the disturbance of the normal shock at the incipient separation Mach number mentioned earlier. As mentioned earlier, shock reflection at M = 1.6 may be related to incipient separation. Therefore two additional test cases were planned with different Mach numbers. ITAM conducted an M = 1.5 test case, and TUD an M = 1.7 test case. These partners have also previously made very specialized and successful contributions to the UFAST project.

Original languageEnglish
Title of host publicationTransition Location Effect on Shock Wave Boundary Layer Interaction
EditorsP. Doerffer
Number of pages103
ISBN (Electronic)978-3-030-47461-4
ISBN (Print)978-3-030-47460-7
Publication statusPublished - 2021

Publication series

NameNotes on Numerical Fluid Mechanics and Multidisciplinary Design
ISSN (Print)1612-2909
ISSN (Electronic)1860-0824

Bibliographical note

Green Open Access added to TU Delft Institutional Repository ‘You share, we take care!’ – Taverne project https://www.openaccess.nl/en/you-share-we-take-care
Otherwise as indicated in the copyright section: the publisher is the copyright holder of this work and the author uses the Dutch legislation to make this work public.

Cite this