Boundary Layer Transition on a Generic Model of Control Flaps in Hypersonic Flow

Madlen Leinemann

ISBN 10: 3961169608 / ISBN 13: 9783961169603

Published by Diplom.de, 2022

About this Item

Boundary Layer Transition on a Generic Model of Control Flaps in Hypersonic Flow | Madlen Leinemann | Taschenbuch | Kartoniert / Broschiert | Englisch | 2022 | [.] | EAN 9783961169603 | Verantwortliche Person für die EU: Dryas Verlag, ein Imprint der Bedey und Thoms Media GmbH, Hermannstal 119k, 22119 Hamburg, kontakt[at]dryas[dot]de | Anbieter: preigu.

Seller Inventory # 122208006

Bibliographic Details

• Title: Boundary Layer Transition on a Generic Model of Control Flaps in Hypersonic Flow
• Publisher: Diplom.de
• Publication Date: 2022
• Language: English
• ISBN 10: 3961169608
• ISBN 13: 9783961169603
• Binding: Taschenbuch
• Condition: Neu
• Dimensions: 210W x 148H x 7D millimeters 210 millimeters width by 148 millimeters height by 7 millimeters depth
• Weight: 146 grams
• Seller catalogs:
  • Bücher

About this title

Synopsis

In the present thesis, experimental and numerical investigations were performed to study boundary layer transition on a generic model of a control surface in hypersonic flow at Mach 6. Experiments were carried out in the Hypersonic Ludwieg Tube at TU Braunschweig (HLB) and in the BAM6QT at Purdue University. In order to investigate the influence of the deflection angle, the Reynolds number and the leading edge radius, flow visualizations (Schlieren), pressure and heat transfer measurements were applied. In the BAM6QT at Purdue University, experiments were carried out under noisy and quiet flow conditions to allow investigations on the influence of the free stream conditions. It was found, that particularly the leading edge bluntness has a great impact on the recirculation region. For the investigated nose radii of rn = 30µm - 330µm, a strong increase of the separation bubble size was observed for increasing nose bluntness. Numerical investigations were performed based on RANS equations. For the HLB measurements, experimental data in combination with stability analysis revealed the presence of second mode instabilities on the cylinder section in the attached boundary layer. Within the flow separation, a shift in frequency was observed to a frequency range typical for first mode instabilities. Due to the lack of a numerical stability analysis for oblique waves the presence of first modes can not be proven. In the Purdue measurements, second modes could not be observed.