Analysis of the Boundary Layer on a Highly Flexible Wing Based on Infrared Thermography Measurements

Book chapter (2024)

Authors

C. Mertens Aerodynamics - Aerospace Engineering
A. Grille Guerra Aerodynamics - Aerospace Engineering
B.W. van Oudheusden Aerodynamics - Aerospace Engineering
Michael Fehrs Deutsches Zentrum für Luft- und Raumfahrt (DLR)
Markus R. Ritter Deutsches Zentrum für Luft- und Raumfahrt (DLR)
Research Group
Aerodynamics (Aerospace Engineering) (TU Delft)
Copyright: © 2024 C. Mertens, A. Grille Guerra, B.W. van Oudheusden, Michael Fehrs, Markus R. Ritter
DOI: https://doi.org/10.1007/978-3-031-40482-5_1
More Info
expand_more

Published Date

2024

Language

English

Reuse Rights

Other than for strictly personal use, it is not permitted to download, forward or distribute the text or part of it, without the consent of the author(s) and/or copyright holder(s), unless the work is under an open content license such as Creative Commons.

Faculty

Aerospace Engineering

Department

Flow Physics and Technology

Research Group

Aerodynamics

Abstract

The effects of the wing skin distortion on the boundary layer of a highly flexible wing are analyzed in a wind tunnel experiment using infrared thermography measurements. Considerable differences in the boundary layer flow are observed when comparing the sections of the wing near the ribs, where the design shape of the wing is preserved, and in between the ribs. At the spanwise locations between the ribs, the sectional wing shape distorts and triggers boundary layer transition close to the leading edge. The differences between the design behavior of the wing and the experimental results of the boundary layer analysis demonstrate the need for considering the skin deformation and its effects on the boundary layer flow when designing highly flexible wings.

Files

978_3_031_40482_5_1.pdf
(.pdf | 1.54 Mb)
- Embargo expired in 01-04-2024