INVESTIGATION OF HEMISPHERICAL AEROSPIKE FOR BLUNT BODY AT HYPERSONIC SPEED

Computational Fluid Dynamics

Aerospace vehicles, such as re-entry vehicles, satellite launching vehicles, missiles, and rockets, operate at extremely high speeds, leading to the generation of shock waves and significant heat and drag. The high heat and drag generation significantly affect the efficiency and maneuverability of such vehicles. To counter this, the present study focuses on the design and analysis of drag reduction techniques for hypersonic vehicles, specifically investigating the effectiveness of different spikes with hemispherical aerodisk. The blunt body configuration is employed as a model, and the analysis is conducted at a hypersonic speed corresponding to Mach number 6. The research explores the impact of varying sizes of spiked blunt bodies, considering the length of the spike to diameter of the blunt body (L/D) ratios of 1.5 and 2. The introduction of a front-facing spike effectively reduces the intensity of the bow shock at the front part of the blunt body by converting it to an oblique shock wave. Notably, a drag reduction of 60% is achieved using a spike with an L/D ratio of 1.5, while a higher reduction of 75% is attained with an L/D ratio of 2. Additionally, the study examines the influence of altering the minor radius of the aerodisk, further evaluating its effect on reduction of the shock wave formation in the frontal region of the aerospike. The findings highlight the potential of these drag reduction techniques to enhance the aerodynamic performance of hypersonic aerospace vehicles, paving the way for improved efficiency and maneuverability in high-speed flight conditions.

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