In this work, separation due to the interaction of normal shock with wall boundary layers in a supersonic duct flow is studied using schlieren, oil flow visualization, and pressure measurements. This study uses separation control devices on three walls of a rectangular duct and investigates the influence of adding control on one wall and on the other walls. It was found that control on any wall has effect on separation on other walls. This effect was found to be due to the change in the size of corner separations. Pressure recovery was found to be steeper with the introduction of more control devices in the duct.
SunZ. Micro vortex generators for boundary layer control: Principles and applications. Int J Flow Control2015; 7: 67–86.
9.
BabinskyHLiYFordCWP. Microramp control of supersonic oblique shock-wave/boundary-layer interactions. AIAA J2009; 47: 668–675.
10.
SunZSchrijerFFJScaranoFet al.The three-dimensional flow organization past a micro-ramp in a supersonic boundary layer. Phys Fluids2012; 24: 055105–055105.
11.
SunZScaranoFVanoudheusdenBWet al.Numerical and experimental investigations of the supersonic microramp wake. AIAA J2014; 52: 1518–1527.
12.
SunZSchrijerFFJScaranoFet al.Decay of the supersonic turbulent wakes from micro-ramps. Phys Fluids2014; 26: 025115–025115.
13.
HergesTKroekerEElliottGet al.Microramp flow control of normal shock/boundary-layer interactions. AIAA J2010; 48: 2529–2542.
14.
TitchenerNBabinskyH. Micro vortex generators applied to flow field containing a normal shock wave and diffuser. AIAA J2011; 49: 1046–1056.
15.
LeeSLothEBabinskyH. Normal shock boundary layer control with various vortex generator geometries. Comput Fluids2011; 49: 233–246.
16.
RybalkoMBabinskyHLothE. Vortex generators for a normal shock/boundary-layer interaction with a downstream diffuser. J Propul Power2012; 28: 71–82.
17.
Vaisakh S and Muruganandam TM. Control of boundary layer separation in supersonic flow using injection through micro ramps. In: Proceedings of the 30th international symposium on shock waves, Israel, 19–24 July, 2015.
18.
SouvereinLJDebièveJF. Effect of air jet vortex generators on a shock wave boundary layer interaction. Exp Fluids2010; 49: 1053–1064.
19.
SzwabaR. Comparison of the influence of different air-jet vortex generators on the separation region. Aerosp Sci Technol2011; 15: 45–52.
20.
ChidambaranathanMVermaSBRathakrishnanE. Control of incident shock-induced boundary-layer separation using steady micro-jet actuators at M∞ = 3.5. Proc IMechE, Part G: J Aerospace Engineering2018, pp. 1–23.
21.
Anderson B, Tinapple J and Surber L. Optimal control of shock wave turbulent boundary layer interactions using micro-array actuation. In: 3rd AIAA flow control conference, 2006, AIAA Paper 2006-3197. Reston, VA: AIAA.
22.
TitchenerNBabinskyH. Shock wave/boundary-layer interaction control using a combination of vortex generators and bleed. AIAA J2013; 51: 1221–1233.
