Numerical Studies of a Supersonic Fluidic Diverter Actuator for Flow Control

Gökoğlu, Süleyman A.; Kuczmarski, Maria A.; Culley, Dennis E.; Raghu, S.

doi:10.2514/6.2010-4415

Cited by 27 publications

(19 citation statements)

References 14 publications

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“…The fluidic actuators under consideration here are closely related to the ones examined by Gokoglu et al [8][9][10] The primary difference in the current configuration is the absence of the divider section used in their work to create twin outlets for the fluid to exit. In the current configuration, which is simpler to fabricate and is being used in several practical applications, the jet comes out of a single outlet, as sketched in Fig.…”

Section: Configurationsmentioning

confidence: 99%

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Numerical Simulation of Fluidic Actuators for Flow Control Applications

Vatsa

Köklü

Wygnanski

et al. 2012

6th AIAA Flow Control Conference

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Active flow control technology is finding increasing use in aerospace applications to control flow separation and improve aerodynamic performance. In this paper we examine the characteristics of a class of fluidic actuators that are being considered for active flow control applications for a variety of practical problems. Based on recent experimental work, such actuators have been found to be more efficient for controlling flow separation in terms of mass flow requirements compared to constant blowing and suction or even synthetic jet actuators. The fluidic actuators produce spanwise oscillating jets, and therefore are also known as sweeping jets. The frequency and spanwise sweeping extent depend on the geometric parameters and mass flow rate entering the actuators through the inlet section. The flow physics associated with these actuators is quite complex and not fully understood at this time. The unsteady flow generated by such actuators is simulated using the lattice Boltzmann based solver PowerFLOW R . Computed mean and standard deviation of velocity profiles generated by a family of fluidic actuators in quiescent air are compared with experimental data. Simulated results replicate the experimentally observed trends with parametric variation of geometry and inflow conditions. Nomenclature

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Section: Configurationsmentioning

confidence: 99%

“…Flow characteristics of similar actuators have been examined by Gokoglu et al in a series of papers. [8][9][10] These will be referred to as Type I, 124D and 90D actuators, or for simplicity as 124D and 90D actuators.…”

Section: Configurationsmentioning

confidence: 99%

Numerical Simulation of Fluidic Actuators for Flow Control Applications

Vatsa

Köklü

Wygnanski

et al. 2012

6th AIAA Flow Control Conference

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show abstract

“…A further increase in flowrate may only cause internal choking and increase in density of the emitted jet without further increase in U jet . Although numerical studies [51] suggest that sweeping jets may be emitted at supersonic speed, it is yet to be verified experimentally with a similar actuator geometry. On a larger scale, single actuator Raman et al [41] achieved supersonic jet velocities which were calculated based on the pressure ratio assuming isentropic expansion.…”

Section: Characterization Of Actuators 41mentioning

confidence: 99%

“…The characteristics of various actuator types, conceptually similar to the designs shown in Figure 1, have been investigated experimentally [31][32][33][41][42][43][44][45][46][47][48] and numerically [48][49][50][51][52] by numerous researchers. Several active and passive concepts to provide the oscillatory character of the emitted jet have been proposed, including selfinduced feedback [43] and external control [42,[44][45][46][47] designs.…”

Section: Introductionmentioning

confidence: 99%

Parameters Governing Separation Control with Sweeping Jet Actuators

Woszidlo

2011

29th AIAA Applied Aerodynamics Conference

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“…Special attention is given to maintain numerical accuracy by allowing sufficient temporal resolution and employing solution-adaptive dynamic grid refinement based on local pressure gradients in order to accurately capture and resolve the shocks (Ref. 14). The solution algorithm is also accordingly adjusted to allow a more robust convergence scheme (Ref.…”

Section: Methods 1: Choking the Array By Pressure Pulsingmentioning

confidence: 99%