Tangential blowing for control of strong normal shock - Boundary layer interactions on inlet ramps

Schwendemann, Myles F.; Sanders, B. W.

doi:10.2514/6.1982-1082

Cited by 10 publications

(4 citation statements)

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“…Early research efforts with passive control methods utilized cavities and/or porous surfaces [87][88][89][90][91][92], ventilation [93], and "pressure plateaus" [94]. Early research efforts with active control methods employed wall jets [95], boundary layer bleeding [96], tangential blowing [97,98], and wall suction [90,92,98].…”

Section: Shock Wave Interaction Control Investigationsmentioning

confidence: 99%

Recent investigations of shock wave effects and interactions

et al. 2020

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Despite over fifty years of research on shock wave boundary layer effects and interactions, many related technical issues continue to be controversial and debated. The present survey provides an overview of the present state of knowledge on such effects and interactions, including discussions of: (i) general features of shock wave interactions, (ii) test section configurations for investigation of shock wave boundary layer interactions, (iii) origins and sources of unsteadiness associated with the interaction region, (iv) interactions which included thermal transport and convective heat transfer, and (v) shock wave interaction control investigations. Of particular interest are origins and sources of low-frequency, large-scale shock wave unsteadiness, flow physics of shock wave boundary layer interactions, and overall structure of different types of interactions. Information is also provided in regard to shock wave investigations, where heat transfer and thermal transport were important. Also considered are investigations of shock wave interaction control strategies, which overall, indicate that no single shock wave control strategy is available, which may be successfully applied to different shock wave arrangements, over a wide range of Mach numbers. Overall, the survey highlights the need for additional understanding of fundamental transport mechanisms, as related to shock waves, which are applicable to turbomachinery, aerospace, and aeronautical academic disciplines.

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Section: Shock Wave Interaction Control Investigationsmentioning

confidence: 99%

Recent investigations of shock wave effects and interactions

et al. 2020

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“…Many aircraft use a boundary-layer diverter system such as the one shown in Fig. Some of the alternate bleeding methods that have been used to control the interaction are tangential blowing (Schwendemann and Sanders, 1982), conventionally sized vortex generators (VGs) (Mounts and Barber, 1992) and some more recent passive and active techniques including: slots (Holden and Babinsky, 2003), low-profi le, micro-VGs (Lin, 2002), and mesofl aps (Hafenrichter et al, 2001). By design, forebody-induced boundary-layer or fl ow separation is diverted away from the inlet.…”

Section: Application To the Inlet Aperture: Shock/boundary Layermentioning

confidence: 99%

Fundamentals and Applications of Modern Flow Control

Joslin¹,

Miller²,

Miller³

2009

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“…Either a blower or the pressure differential that exits in the passage is utilized to inject the fluid into the retarded region of the boundary layer. Schwendemann and Sanders (1982) showed that the efficiency of the fluid injection depends on the momentum of the injected fluid and the distance between the injection slit and the boundary layer separation point. It is indicated that for the injection to be effective, this distance must be long enough to allow sufficient time for the mixing process to facilitate the momentum transfer from the jet to the boundary layer.…”

Section: Boundary-layer Control By Fluid Injectionmentioning

confidence: 99%

Simulation of Flow in Turbopump Vaneless and VanedDiffusers with Fluid Injection

Ogut

Pastor

1998

International Journal of Rotating Machinery

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In future space missions by NASA there will be a need for “Space Transfer Vehicles” to perform varying orbital transfers and descents. This requires engines capable of producing different levels of thrust. To accomplish this, the turbopumps employed in these engines should efficiently provide a wide range of flow outputs. However, current fuel and oxidizer turbopumps with vaned diffusers do not perform efficiently at off-design (low) flow rates mainly due to flow separation in the vaned diffuser.This paper evaluates the effectiveness of boundary layer control by fluid injection (blowing) for suppressing or eliminating the flow separation in a vaned diffuser. A 3-D flow model including vaneless and vaned diffusers of a liquid hydrogen (LH2) turbopump is studied using the CFD code FIDAP. The paper presents the results of the model at design and offdesign flow conditions.The model results showed that flow separation occurs at the top or suction surface of the vaneless diffuser and at the bottom or pressure surface of the vaned diffuser at off-design flow rates. When fluid injection was applied through the bottom surface of the vaned diffuser, the separated flow region was reduced almost entirely, resulting in an increase in pressure recovery of up to 21% with varying fluid injection rates. Results also showed that there is an optimum injection rate which is most effective in reducing or eliminating the region of flow separation.

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Tangential blowing for control of strong normal shock - Boundary layer interactions on inlet ramps

Cited by 10 publications

References 0 publications

Recent investigations of shock wave effects and interactions

Recent investigations of shock wave effects and interactions

Fundamentals and Applications of Modern Flow Control

Simulation of Flow in Turbopump Vaneless and VanedDiffusers with Fluid Injection

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