Effect of Jet Spacing on Swept-Wing Leading-Edge Separation Control

Walker, Michael M.; Hipp, Kyle D.; Benton, Stuart I.; Bons, Jeffrey P.

doi:10.2514/1.j056352

Cited by 5 publications

(2 citation statements)

References 10 publications

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“…On the other hand, the experimental study by Walker et al 91 investigates the possibilities of semi-active flow control on swept wings via discrete jets that steadily eject fluid normal to the suction surface. It appears there are benefits, but further research is necessary.…”

Section: Classification and Description Of Flow Control Methodsmentioning

confidence: 99%

Current state and future trends in boundary layer control on lifting surfaces

Svorcan

Wang

Griffin

2022

Advances in Mechanical Engineering

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Successful flow control may bring numerous benefits, such as flow stabilization, flow reattachment, separation delay, drag reduction, lift increase, aerodynamic performance improvement, energy efficiency increase, shock delay or weakening, noise reduction, etc. For these purposes, many different flow control devices, which can be classified as passive, semi-active and active, have been designed and tested. This review paper aims to highlight the most promising and commonly employed boundary layer control methods as well as outline their potential in specific applications in aerospace and energy engineering. Referenced studies, performed on various geometries (flat plates, channels, airfoils, wings, blades, cylinders), are primarily numerical or experimental. Although enhanced aerodynamic performance is achieved in many cases, further research is required to draw general conclusions. This paper aims to demonstrate that, in the future, we may expect further developments of flow control actuators, as well as their increased application.

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Section: Classification and Description Of Flow Control Methodsmentioning

confidence: 99%

Current state and future trends in boundary layer control on lifting surfaces

Svorcan

Wang

Griffin

2022

Advances in Mechanical Engineering

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“…Therefore, unsteady flow control has been widely considered due to the lower power and momentum requirements compared to the steady flow control method. In unsteady flow control, several parameters affect the separation control on lifting surfaces, including geometric and physical parameters (Bauer, 2015;Hipp et al, 2016) of the main flow (Seifert et al, 2004;Haucke and Nitsche, 2013;Wild, 2015) and the actuation system (Stalnov and Seifert, 2010;Taleghani et al, 2012;Hecklau et al, 2013;Feero et al, 2017;Munday and Taira, 2018;Walker et al, 2018).…”

Section: Introductionmentioning

confidence: 99%

Effects of low and high frequency actuation on aerodynamic performance of a supercritical airfoil

Abdolahipour

2023

Front. Mech. Eng.

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The main objective of this study is to investigate the effects of low and high frequency actuation in improving the aerodynamic performance of the supercritical airfoil with the approach of using it in a high-lift or flight control device. For this purpose, a flow control numerical simulation is performed on a supercritical airfoil with NASA SC(2)-0714 cross section using a pulsed jet at the chord-based Reynolds number of 1 × 106. The pulsed jet actuation with different reduced frequencies of 0.2, 1, 1.2, 2.4, 4, 6, and 12 is implemented on the upper side of the airfoil surface upstream of the separation point of the uncontrolled case. The aerodynamic efficiency improvements are investigated by extracting the results of time-averaged and instantaneous aerodynamic forces for all cases. The study compares the flow streamline, Q-criterion contour, and surface pressure distribution to examine how the separated flow configuration over the airfoil responds to different actuation frequencies. The results indicate that pulsed jet actuation effectively postpones the flow separation. A comparison of the time-averaged aerodynamic coefficients at different actuation frequencies revealed that utilizing a low actuation frequency range maximizes lift, while a high frequency range minimizes drag. In addition, the aerodynamic efficiency of the supercritical airfoil improves across all controlled scenarios, with the optimal increase in aerodynamic efficiency of 28.62% achieved at an actuation frequency of F+ = 1.

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