Influence of Nose Cone Fairing and Spike on Supersonic Blunt Body Flows

被引：2

作者：

Sarwar, Md. G. ^{[1
]}

Kumar, Priyank ^{[1
]}

Das, Sudip ^{[1
]}

机构：

[1] Birla Inst Technol, Dept Space Engn & Rocketry, Ranchi, Jharkhand 835215, India

来源：

JOURNAL OF SPACECRAFT AND ROCKETS | 2024年 / 61卷 / 01期

关键词：

NUMERICAL HEAT-TRANSFER; DRAG REDUCTION; HYPERSONIC FLOW; HIGH-SPEED; DRIVING MECHANISMS; FLUX REDUCTION; BODIES; SIMULATION;

D O I：

10.2514/1.A35757

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Experiments and computations were performed at Mach number 2.0 for various nose cone fairing bodies with a sharp spike and conical spike of L/Dratio = 1.0 and with a sharp spike having a fixed tip location of different L/D ratios. Attempts were made to alter the flowfield of various nose cone fairing bodies with the adoption of the spike. Qualitative and quantitative measurement studies indicate the changes that support the reduction of drag forces, not only on hemispherical blunt bodies but also on various nose cone fairings. This drag reduction with the configurations tested in this study indicates the importance of the region between the spike and the blunt-body face. The results presented here justify the quality and quantity of recirculating flow and its implication for drag reduction.

引用

页码：200 / 216

页数：17

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