Boundary-layer characteristics and effects of threadlike roughness for a high-slenderness projectile
Publication date
2025-12-21
Document type
Research article
Author
Organisational unit
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Series or journal
Journal of Spacecraft and Rockets
ISSN
Periodical volume
63
Periodical issue
3
First page
789
Last page
804
Peer-reviewed
✅
Part of the university bibliography
✅
Language
English
DDC Class
004 Informatik
500 Naturwissenschaften
600 Technik
Keyword
Boundary layer
Roughness
Aerodynamics
Transition
Projectile
Abstract
The aerodynamic properties of high-slenderness finned projectiles with and without a threadlike roughness element on the shaft were evaluated. The alteration of the aerodynamic coefficients of the longitudinal motion due to the surface roughness were investigated by means of strain gauge balance and free-oscillation measurements in a supersonic blowdown wind tunnel. The test conditions cover a Mach number range from 2.5 to 4.1 at diameter-based Reynolds numbers from 2 x 10⁵ to 1 x 10⁶. The forebody axial force was found to be significantly increased by the thread element with the deviations compared to the smooth-shaft case growing overproportionately with increasing angle of attack. Whereas a minor influence by the thread element was observed for the normal force, the pitching moment is significantly altered by the thread element. Flow visualizations by single frame as well as videographic schlieren setups gave insights into the underlying flow physics. The overall flow topology, the boundary-layer thickness, the laminar-turbulent of the boundary layer, the separation of the flow at high angles of attack, and the interaction between the boundary layer and the individual thread elements were captured.
Cite as
Boundary-Layer Characteristics and Effects of Threadlike Roughness for a High-Slenderness Projectile Sebastian Michalski, Robert Hruschka, Daniel Klatt, Myriam Bastide, and Michael Breuer Journal of Spacecraft and Rockets 2026 63:3, 789-804
Version
Published version
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