Abstract
In high-speed fluid dynamics, base pressure controls find many engineering applications, such as in the automobile and defense industries. Several studies have been reported on flow control with sudden expansion duct. Passive control was found to be more beneficial in the last four decades and is used in devices such as cavities, ribs, aerospikes, etc., but these need additional control mechanics and objects to control the flow. Therefore, in the last two decades, the active control method has been used via a microjet controller at the base region of the suddenly expanded duct of the convergent–divergent (CD) nozzle to control the flow, which was found to be a cost-efficient and energy-saving method. Hence, in this paper, a systemic literature review is conducted to investigate the research gap by reviewing the exhaustive work on the active control of high-speed aerodynamic flows from the nozzle as the major focus. Additionally, a basic idea about the nozzle and its configuration is discussed, and the passive control method for the control of flow, jet and noise are represented in order to investigate the existing contributions in supersonic speed applications. A critical review of the last two decades considering the challenges and limitations in this field is expressed. As a contribution, some major and minor gaps are introduced, and we plot the research trends in this field. As a result, this review can serve as guidance and an opportunity for scholars who want to use an active control approach via microjets for supersonic flow problems.
Highlights
In supersonic vehicles, the flow of exit from the rockets and missile engines has become a significant issue
Researchers have used a high-speed nozzle with a sudden expansion duct and a microjet controller; a tiny hole in the base area is drilled to control the flow, which was found to be an excellent technique in a supersonic flow problem
Patel et al [122] derived the principles of the de Laval nozzle, using the nozzle operating theory, and examined the experimental approach of evaluating flow for various nozzles; the variance of flow parameters, such as pressure, temperature, velocity, and density, was visualized [123] to investigate the effects of geometry and flow parameters on the thrust force created by the flow from the CD nozzles to a circular duct with a larger cross-section
Summary
The flow of exit from the rockets and missile engines has become a significant issue. Many studies have reported controlling the high-speed flows as a passive and active control method. The active control of high-speed flow has been studied extensively over the last two decades. Researchers have used a high-speed nozzle with a sudden expansion duct and a microjet controller; a tiny hole in the base area is drilled to control the flow, which was found to be an excellent technique in a supersonic flow problem. The abrupt expansion of the external compressible flow over the back of the projectiles and its association to the base pressure has long been the focus of researchers’ interest. The. The abrupt expansion of the external compressible flow over the back of the projectiles and its association to the base pressure has long been the focus of researchers’ bainsetedrersatg.,Twhheicbhasaeccdoruangt,swfohricahsaigcncoifiucnatnstfpororatiosingnoiffitchaenot vpeorratlilodnraogf ,tihsedoevteerrmalilnderdagb,yis thdeebtearsme ipnreedssbuyret.heGbenaseeraplrlye,ssthuereb.aGsenperreaslslyu,rtehfeobr aashe ipgrhe-ssspuereedfoprroajehcigtihle-sipseleodwperotjheactnile thies alomwbeierntthparnestshuerea.mTbhieenvtasptrmesasjuorreit.yTohfethveasbtalmlisatjiocrsittyesot fdathtae wbaelrleisstuicpsptleiestd,dlaetaadiwnegre usutoppplriedsu, mleaedtihnagt uthsetobpasrespurmesestuhraetrtahteiobadseeppernedssuernetirraetliyo doneptehnedflsiegnhttirMelaycohnntuhme fbliegrh. The effect of nozzle geometry on the high-velocity oxygen fuel (HVOF) system was calculated [22]; the nozzle attached inside were adjusted, and they proved that the cold spray technique influences the HVOF system and applies to the nozzle configuration
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