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2021 | OriginalPaper | Chapter

Analysis of Vortex Burst Phenomena on Generic Hybrid Delta Wing Planforms at Subsonic Speeds

Authors : Dominik Sedlacek, Florian M. Heckmeier, Artur Usbek, Christian Breitsamter

Published in: New Results in Numerical and Experimental Fluid Mechanics XIII

Publisher: Springer International Publishing

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Abstract

In this study, experimental investigations are performed to analyze the vortex behavior and breakdown characteristics on a generic multiple swept wing fuselage configuration. Fast Response Aerodynamic Pressure Probe and Particle Image Velocimetry measurements are performed in the low-speed wind tunnel W/T-A facility of the Chair of Aerodynamics and Fluid Mechanics at the Technical University of Munich. The experiments are executed at subsonic speed, symmetric freestream conditions and angles of attack of \(\alpha = 16^\circ , 24^\circ \) and \(32^\circ \). In a power spectral density analysis of velocity fluctuations helical mode instabilities and shear layer instabilities can be detected.

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previous chapter Steady-State Flow Solutions for Delta Wing Configurations at High Angle of Attack Using Implicit Schemes

next chapter Numerical Modelling of a Wind Tunnel Experiment to Investigate Vortex-Dominated Flow at Medium and High Angles of Attack

Kölzsch A.: Active Flow Control of Delta Wing Leading-Edge Vortices. Dissertation, Technical University Munich (2017)

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Pfnür, S., Breitsamter, C.: Leading-edge vortex interactions at a generic multiple swept-wing aircraft configuration. J. Aircraft 56(6), 2093–2107 (2019). https://doi.org/10.2514/1.C035491CrossRef

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Title: Analysis of Vortex Burst Phenomena on Generic Hybrid Delta Wing Planforms at Subsonic Speeds
Authors: Dominik Sedlacek
Florian M. Heckmeier
Artur Usbek
Christian Breitsamter
Publisher: Springer International Publishing
Book: New Results in Numerical and Experimental Fluid Mechanics XIII
Print ISBN: 978-3-030-79560-3

Electronic ISBN: 978-3-030-79561-0

Copyright Year: 2021
DOI: https://doi.org/10.1007/978-3-030-79561-0_27

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