Design exploration on the drag reduction and thermal protection over a blunted waverider with multiple opposing jets

Chen, Ji; Liu, Bing; Huang, Wei; Li, Shibin; Meng, Zhao-e; Yan, Li; Choubey, Gautam

doi:10.1016/j.ast.2022.107519

Cited by 11 publications

(3 citation statements)

References 33 publications

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“…The increasing jet pressure ratio and lateral jet ratio decrease both drag and heat flux. Ji et al (2022) numerically studied the influence of opposing jets on aerodynamic performance and thermal protection on blunt body. It was found that the opposing jet method significantly reduces the drag and aerodynamic heating.…”

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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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: 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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“…In the aerospace and automotive context, Aerodynamic heating is known as the process of heating near the solid body due to change of the hypersonic/supersonic flow into energy term 1 , 2 . Although it seems that the transformation of momentum into thermal energy is simple process, its impacts on the flow are highly complicated 3 – 5 .…”

Section: Introductionmentioning

confidence: 99%

Influence of lateral single jets for thermal protection of reentry nose cone with multi-row disk spike at hypersonic flow: computational study

Shi

Cheng

Alizadeh

et al. 2023

Sci Rep

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The main challenge for the advancement of current high-speed automotives is aerodynamic heating. In this study, the application of lateral jet for thermal protection of the high-speed automotives is extensively studied. The simulation of the lateral coolant jet is done via Computational fluid dynamic at high-velocity condition. Finding optimum jet configuration for reduction of the aerodynamic heating is the main goal of this research. Two different coolant jets (Helium and Carbon dioxide) are investigated as coolant jet and flow study and fuel penetration mechanism are fully presented. In addition, the thermal load on the main body of nose cone is compared for different configurations. Our results specify that the injection of lateral jet near the tip of spike is effective for thermal protection of main body via deflection of bow shock. Also, Carbon dioxide jet with lower diffusivity is more effective for the protection of forebody with multi-row disk from sever aerodynamic heating.

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“…The importance of the forebody design for developing of the current hypersonic vehicle is undeniable and unavoidable 1 , 2 . The formation of a strong compression shock wave results in the heat source burning the nose of the high-speed vehicles this phenomenon is known as Aerodynamic heating which has a severe disadvantageous on the performance of supersonic vehicles and the management of the design for the body is highly important since these two factors are connected to each other 3 , 4 .…”

Section: Introductionmentioning

confidence: 99%

Influence of coolant multi-jets on heat reduction of nose cone with blunt spike at hypersonic flow

Ghanbari

Maddah

Alinejad

2022

Sci Rep

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The importance of the cooling system for the design of the forebody of high-speed vehicles is significant due to severe aerodynamic heating at hypersonic flight. In the present study, injection of multi and single-coolant jets on the thermal performance of forebody design of nose cone with the cut spike is thoroughly investigated at hypersonic flow. A three-dimensional model of the blunt cone is presented for computational investigations of proposed jet and spike configurations. Injection of two coolant gasses (Helium and carbon dioxide) into the cooling system of the nose cone with a blunt spike is investigated. Three locations for both opposing and lateral jets are compared to find the efficient jet location. Our results indicate that a single lateral jet injected from the tip of the spike is more efficient for heat reduction. A comparison of the multiple injection system also shows that the heat reduction of the helium gas is about 15% more than CO2 jets.

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Design exploration on the drag reduction and thermal protection over a blunted waverider with multiple opposing jets

Cited by 11 publications

References 33 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

Influence of lateral single jets for thermal protection of reentry nose cone with multi-row disk spike at hypersonic flow: computational study

Influence of coolant multi-jets on heat reduction of nose cone with blunt spike at hypersonic flow

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