Aerodynamic characterization of a hypersonic projectile using acceleration-based measurements and numerical methods
Publication date
2024-10-01
Document type
Research article
Author
Organisational unit
Publisher
American Institute of Aeronautics and Astronautics
Series or journal
Journal of Spacecraft and Rockets
ISSN
Periodical volume
62
Periodical issue
2
First page
477
Last page
493
Peer-reviewed
✅
Part of the university bibliography
✅
Language
English
DDC Class
004 Informatik
500 Naturwissenschaften
600 Technik
Keyword
Hypersonic projectile
Acceleration-based measurements
Wind tunnel experiments
Transition
Abstract
Armor-piercing fin-stabilized projectiles stand out by their exceptionally high slenderness ratios and ground-level flight at super- and hypersonic speeds. As space constraints limit the integration of measurement equipment into such slender test models, nonintrusive measurement techniques become favorable. The present analysis demonstrates a renewed approach to the free-flight technique, which sets models into unconstrained flight through the test section. It enabled the evaluation of the quasi-steady drag, lift, and pitching moment characteristics, and, to some extent, also the dynamic pitch damping characteristics. An alternative to the free-flight technique is the free-oscillation technique, which limits the motion to a rotation around the center of gravity. The free-oscillation technique allowed a higher-fidelity analysis of the static and dynamic pitching moments. Both methods were based on the analysis of the accelerations derived from trajectory tracking. This acceleration-based approach enabled the evaluation of the highly nonlinear characteristics. The high slenderness of the investigated projectile leads to a significant contribution of the viscous forces to the overall drag. These viscous forces are sensitive to the laminar-turbulent boundary-layer state, as well as the thermal boundary conditions. The application of a high-resolution schlieren system enabled the assessment of the local laminar-turbulent boundary-layer state, while the use of low- and high-enthalpy testing facilities enabled the assessment of the aerothermal influence. Steady-state Reynolds-averaged Navier–Stokes simulations, which included laminar-turbulent transition modeling, were employed to replicate the results of the experimental efforts.
Cite as
Journal of Spacecraft and Rockets, 62(2), 477-493, (2025)
Version
Published version
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