Dynamic Drag Reduction Effects of Aerospikes and Aerodisks

Han, Rong; Liu, Wei; Yang, Xiaoliang; Chang, Xinghua

doi:10.1155/2021/9370331

Cited by 2 publications

(3 citation statements)

References 18 publications

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“…Based on the comparison between the previous and present studies, the percentage of drag coefficient variation was obtained at 2.78% and 2.37%, respectively. However, the error bar of 3% was acceptable with respect to the reference, Han et al (2021).…”

Section: Solver and Grid Independencementioning

confidence: 89%

“…The results show that the coefficients of drag for intermediate and sharp aerospikes were 0.40 and 0.51, respectively. Han et al (2021) investigated the effects of aerospike length (L/D ¼ 1.0, 1.5 and 2.0) with an inverted conical aerodisk diameter (d/D ¼ 0.25 to 0.75 in steps of 0.0625). The variation in L/D does not show much impact on drag reduction.…”

Section: Introductionmentioning

confidence: 99%

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Aero-spike and aero-disk effects of on wave drag reduction of supersonic flow past over blunt body

Balusamy,

A.,

2024

AEAT

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Purpose The purpose of this study is to explore the effects of aerospike and hemispherical aerodisks on flow characteristics and drag reduction in supersonic flow over a blunt body. Specifically, the study aims to analyze the impact of varying the length of the cylindrical rod in the aerospike (ranging from 0.5 to 2.0 times the diameter of the blunt body) and the diameter of the hemispherical disk (ranging from 0.25 to 0.75 times the blunt body diameter). CFD simulations were conducted at a supersonic Mach number of 2 and a Reynolds number of 2.79 × 106. Design/methodology/approach ICEM CFD and ANSYS CFX solver were used to generate the three-dimensional flow along with its structures. The flow structure and drag coefficient were computed using Reynolds-averaged Navier–Stokes equation model. The drag reduction mechanism was also explained using the idea of dividing streamline and density contour. The performance of the aero spike length and the effect of aero disk size on the drag are investigated. Findings The separating shock is located in front of the blunt body, forming an effective conical shape that reduces the pressure drag acting on the blunt body. It was observed that extending the length of the spike beyond a specific critical point did not impact the flow field characteristics and had no further influence on the enhanced performance. The optimal combination of disk and spike length was determined, resulting in a substantial reduction in drag through the introduction of the aerospike and disk. Research limitations/implications To predict the accurate results of drag and to reduce the simulation time, a hexa grid with finer mesh structure was adopted in the simulation. Practical implications The blunt nose structures are primarily employed in the design of rockets, missiles, and re-entry capsules to withstand higher aerodynamic loads and aerodynamic heating. Originality/value For the optimized size of the aero spike, aero disk is also optimized to use the benefits of both.

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Section: Solver and Grid Independencementioning

confidence: 89%

Section: Introductionmentioning

confidence: 99%

Aero-spike and aero-disk effects of on wave drag reduction of supersonic flow past over blunt body

Balusamy,

A.,

2024

AEAT

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“…Han et al 27 states that the Figure 14 depicts the flow field density contour when the ratios of aerospike length and blunt diameter are 0.5, 1.0 and 2.0. When the pitch angle is small, for example, 0° or 6.67°, the recirculation zone of L/D=0.5 configuration is too small to surround the whole surface of the blunt forebody.…”

Section: Effects Of Aerodisk Shape On Drag Reductionmentioning

confidence: 99%

Higher-Fidelity CFD Tools for Conceptual Design of Supersonic Business Jets

et al. 2022

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Supersonic business jets are regarded as prime modes of next-generation supersonic transport. They allow long-distance travel at low duration by crossing the Mach 1 speed. This results in the breaking of the sound barrier and a sonic boom generated. Sonic boom and aerodynamic efficiency are the biggest concerns for the return of civil supersonic transport. Supersonic vehicles, such as spacecraft, high-speed missiles, and supersonic jets, are subjected to heavy shock wave drag during flight, which will seriously affect the aerodynamic performance of supersonic vehicles. In addition, supersonic vehicles are also subjected to heavy aerodynamic heating during flight. Therefore, modified geometries using aerospikes and aerodisks can be effective to reduce the above-said concerns. In this paper, we discuss aerospikes and aerodisks, its effectiveness, and its importance. The use of these novel mechanisms in the design of supersonic business jets is probed in order to perform future design studies.

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Dynamic Drag Reduction Effects of Aerospikes and Aerodisks

Cited by 2 publications

References 18 publications

Aero-spike and aero-disk effects of on wave drag reduction of supersonic flow past over blunt body

Aero-spike and aero-disk effects of on wave drag reduction of supersonic flow past over blunt body

Higher-Fidelity CFD Tools for Conceptual Design of Supersonic Business Jets

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