{"title":"马赫数对带翼片超音速射流流场和声学的影响","authors":"S. R. Lavala, S. Das","doi":"10.1134/S0015462824604741","DOIUrl":null,"url":null,"abstract":"<p>Experimental investigations are carried out with triangular shaped tabs orientated circumferentially 120° apart with designed nozzle Mach numbers of 1.5, 2.0, and 2.5. The effects of the Mach number with a constant exit pressure ratio (EPR) of 0.35 and the constant nozzle pressure ratio (NPR) of 6 are studied. The Pitot survey and Schlieren flow visualization are carried out to present the jet core length characteristics, the shock cell structure, and the jet spread through time-averaged images. Acoustic measurements are made inside an anechoic chamber to get the signatures of various nozzle design Mach numbers. It is observed that the screech fundamental frequency shifts with increase in the design Mach numbers. The triangular shaped tabs can reduce the jet core length effectively to the tune of 40–70% in the ranges tested at various designed Mach numbers. The results indicate complete alleviation of noise/acoustics for jets adopting tabs having triangle shape irrespective of the penetration depth and orientation.</p>","PeriodicalId":560,"journal":{"name":"Fluid Dynamics","volume":"60 1","pages":""},"PeriodicalIF":0.6000,"publicationDate":"2025-05-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"Influence of the Mach Number on the Flow Field and Acoustics of a Supersonic Jet with Tabs\",\"authors\":\"S. R. Lavala, S. Das\",\"doi\":\"10.1134/S0015462824604741\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"<p>Experimental investigations are carried out with triangular shaped tabs orientated circumferentially 120° apart with designed nozzle Mach numbers of 1.5, 2.0, and 2.5. The effects of the Mach number with a constant exit pressure ratio (EPR) of 0.35 and the constant nozzle pressure ratio (NPR) of 6 are studied. The Pitot survey and Schlieren flow visualization are carried out to present the jet core length characteristics, the shock cell structure, and the jet spread through time-averaged images. Acoustic measurements are made inside an anechoic chamber to get the signatures of various nozzle design Mach numbers. It is observed that the screech fundamental frequency shifts with increase in the design Mach numbers. The triangular shaped tabs can reduce the jet core length effectively to the tune of 40–70% in the ranges tested at various designed Mach numbers. The results indicate complete alleviation of noise/acoustics for jets adopting tabs having triangle shape irrespective of the penetration depth and orientation.</p>\",\"PeriodicalId\":560,\"journal\":{\"name\":\"Fluid Dynamics\",\"volume\":\"60 1\",\"pages\":\"\"},\"PeriodicalIF\":0.6000,\"publicationDate\":\"2025-05-12\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"Fluid Dynamics\",\"FirstCategoryId\":\"5\",\"ListUrlMain\":\"https://link.springer.com/article/10.1134/S0015462824604741\",\"RegionNum\":4,\"RegionCategory\":\"工程技术\",\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"Q4\",\"JCRName\":\"MECHANICS\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"Fluid Dynamics","FirstCategoryId":"5","ListUrlMain":"https://link.springer.com/article/10.1134/S0015462824604741","RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q4","JCRName":"MECHANICS","Score":null,"Total":0}
Influence of the Mach Number on the Flow Field and Acoustics of a Supersonic Jet with Tabs
Experimental investigations are carried out with triangular shaped tabs orientated circumferentially 120° apart with designed nozzle Mach numbers of 1.5, 2.0, and 2.5. The effects of the Mach number with a constant exit pressure ratio (EPR) of 0.35 and the constant nozzle pressure ratio (NPR) of 6 are studied. The Pitot survey and Schlieren flow visualization are carried out to present the jet core length characteristics, the shock cell structure, and the jet spread through time-averaged images. Acoustic measurements are made inside an anechoic chamber to get the signatures of various nozzle design Mach numbers. It is observed that the screech fundamental frequency shifts with increase in the design Mach numbers. The triangular shaped tabs can reduce the jet core length effectively to the tune of 40–70% in the ranges tested at various designed Mach numbers. The results indicate complete alleviation of noise/acoustics for jets adopting tabs having triangle shape irrespective of the penetration depth and orientation.
期刊介绍：
Fluid Dynamics is an international peer reviewed journal that publishes theoretical, computational, and experimental research on aeromechanics, hydrodynamics, plasma dynamics, underground hydrodynamics, and biomechanics of continuous media. Special attention is given to new trends developing at the leading edge of science, such as theory and application of multi-phase flows, chemically reactive flows, liquid and gas flows in electromagnetic fields, new hydrodynamical methods of increasing oil output, new approaches to the description of turbulent flows, etc.
求助内容：
应助结果提醒方式：
京公网安备 11010802042870号
