Stepped aerospike for enhanced drag reduction using multiple intermediate shocks

IF 1.7 4区工程技术 Q3 MECHANICS

Shock Waves Pub Date : 2022-08-18 DOI:10.1007/s00193-022-01093-3

A. D. Kumar, A. Mandal, S. Majumder, S. Saha

{"title":"Stepped aerospike for enhanced drag reduction using multiple intermediate shocks","authors":"A. D. Kumar, A. Mandal, S. Majumder, S. Saha","doi":"10.1007/s00193-022-01093-3","DOIUrl":null,"url":null,"abstract":"<div><p>Drag reduction using aerospikes has been explored extensively due to the consequences associated with the range, manoeuvrability, and structural limitations of supersonic vehicles. The objective of the present work is to introduce steps as a novel aft-geometry configuration for a sharp-tipped aerospike to enhance drag reduction. The conventional and stepped spikes are of aspect ratio 1.5. Axisymmetric viscous flow simulations and wind-tunnel tests are conducted at a Mach number of 2.43 to analyze the drag reduction phenomena. The viscous simulations provide insight into the shock structure and the recirculation zones. Schlieren images obtained from the experiments in the wind tunnel reveal that the shock angles and locations are in reasonable agreement with the viscous flow simulations. The stepped geometry introduces multiple shocks which eventually reduce the strength of the reattachment shock. A detailed comparison of the location of the steps reveals the effect of the recirculation zones and the interaction of oblique shocks and expansion fans on the extent of drag reduction. The simulations indicate that an enhanced reduction in the wave drag ranging from 9.3 to 21.1% may be achieved over a conventional aerospike as the step locations are varied. The maximum drag reduction potential offered by the steps may be realized in practice using an actively adapting telescopic aerospike.</p></div>","PeriodicalId":775,"journal":{"name":"Shock Waves","volume":null,"pages":null},"PeriodicalIF":1.7000,"publicationDate":"2022-08-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"Shock Waves","FirstCategoryId":"5","ListUrlMain":"https://link.springer.com/article/10.1007/s00193-022-01093-3","RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q3","JCRName":"MECHANICS","Score":null,"Total":0}

引用次数: 0

Abstract

Drag reduction using aerospikes has been explored extensively due to the consequences associated with the range, manoeuvrability, and structural limitations of supersonic vehicles. The objective of the present work is to introduce steps as a novel aft-geometry configuration for a sharp-tipped aerospike to enhance drag reduction. The conventional and stepped spikes are of aspect ratio 1.5. Axisymmetric viscous flow simulations and wind-tunnel tests are conducted at a Mach number of 2.43 to analyze the drag reduction phenomena. The viscous simulations provide insight into the shock structure and the recirculation zones. Schlieren images obtained from the experiments in the wind tunnel reveal that the shock angles and locations are in reasonable agreement with the viscous flow simulations. The stepped geometry introduces multiple shocks which eventually reduce the strength of the reattachment shock. A detailed comparison of the location of the steps reveals the effect of the recirculation zones and the interaction of oblique shocks and expansion fans on the extent of drag reduction. The simulations indicate that an enhanced reduction in the wave drag ranging from 9.3 to 21.1% may be achieved over a conventional aerospike as the step locations are varied. The maximum drag reduction potential offered by the steps may be realized in practice using an actively adapting telescopic aerospike.

Abstract Image

查看原文本刊更多论文

阶梯式气动尖峰，使用多重中间冲击增强减阻

由于与超音速飞行器的航程、机动性和结构限制相关的后果，使用气动尖峰减少阻力已经得到了广泛的探索。目前工作的目的是介绍步骤作为一个新的后几何配置的尖头气动刺，以提高减少阻力。常规和阶梯尖峰的纵横比为1.5。在马赫数为2.43的条件下进行了轴对称粘性流动模拟和风洞试验，分析了减阻现象。粘性模拟提供了对激波结构和再循环区域的深入了解。在风洞实验中获得的纹影图像显示，激波角度和位置与粘性流动模拟结果基本吻合。阶梯式几何结构引入了多重冲击，最终降低了再附着冲击的强度。对台阶位置的详细比较揭示了再循环区以及斜冲击和膨胀风机的相互作用对减阻程度的影响。仿真结果表明，随着台阶位置的变化，与传统的气栅相比，波阻的减小幅度可达9.3% ~ 21.1%。在实际应用中，采用主动自适应伸缩气柱可以实现台阶所提供的最大减阻潜力。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

求助全文

约1分钟内获得全文求助全文

来源期刊

Shock Waves 物理-力学

CiteScore

4.10

自引率

9.10%

发文量

审稿时长

17.4 months

期刊介绍： Shock Waves provides a forum for presenting and discussing new results in all fields where shock and detonation phenomena play a role. The journal addresses physicists, engineers and applied mathematicians working on theoretical, experimental or numerical issues, including diagnostics and flow visualization. The research fields considered include, but are not limited to, aero- and gas dynamics, acoustics, physical chemistry, condensed matter and plasmas, with applications encompassing materials sciences, space sciences, geosciences, life sciences and medicine. Of particular interest are contributions which provide insights into fundamental aspects of the techniques that are relevant to more than one specific research community. The journal publishes scholarly research papers, invited review articles and short notes, as well as comments on papers already published in this journal. Occasionally concise meeting reports of interest to the Shock Waves community are published.