Abstract
In order to investigate the dynamic characteristics of blunt aircraft mounted with aerospikes and aerodisks in large-amplitude force-pitching, the Roe spatial scheme and the lower-upper symmetric Gauss-Seidel (LU-SGS) method with dual time step are employed for discretization of unsteady Navier-Stokes (N-S) equations. A parametric investigation on the flow fields is conducted by altering the pitching period, aerospike length, and aerodisk diameter consequently via a variable-controlling procedure. Dynamic characteristics of aerodynamic drag as well as the visualization of unsteady flow fields are achieved, and the results show that the aerodynamics of hypersonic aircraft under the condition of large-amplitude force-pitching vibration have hysteresis characteristics affected by periods of force-pitching vibration. In addition, when changing aerospike length and aerodisk diameter, the variation tendency of drag reduction efficiency is determined by the pitching angle of the oscillation process.
Highlights
When flying at hypersonic speed, aircrafts face problems of excessive drag and severe aerodynamic heating, which greatly reduce the payload of the aircraft [1]
Researches on blunt body drag reduction methods in hypersonic flows have mainly focused on the forwardfacing cavity, the energy deposition, an opposing jet issued at the stagnation point, aerospikes, and their combinatorial configurations [2]
We comprehensively analyze the impact of these parameters on the flow field around the blunt body
Summary
When flying at hypersonic speed, aircrafts face problems of excessive drag and severe aerodynamic heating, which greatly reduce the payload of the aircraft [1]. These issues, posing hidden dangers for the design and flight safety of hypersonic aircraft, address great scientific value and engineering significance to study the mechanism of drag reduction in this context. Researches on blunt body drag reduction methods in hypersonic flows have mainly focused on the forwardfacing cavity, the energy deposition, an opposing jet issued at the stagnation point, aerospikes, and their combinatorial configurations [2]. Due to its simplicity and effectiveness, the aerospike system was applied to the head of the Trident I missile by the Lockheed Martin Corporation (America) and was found to reduce drag by as much as 52% in hypersonic flows [3]
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