Active Flow Control via Discrete Sweeping and Steady Jets on a Simple-Hinged Flap

Melton, LaTunia Pack; Köklü, Mehti; Andino, Marlyn Y.; Lin, John C.

doi:10.2514/1.j056841

Cited by 33 publications

(19 citation statements)

References 26 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The fluidic oscillators at higher C µ is discussed in Refs. [11,12]. The steady blowing also has a logarithmic trend; however, it is less effective than the steady suction or the fluidic oscillators for the entire C µ range.…”

Section: Performance Assessment Of Fluidic Oscillatorsmentioning

confidence: 99%

Performance Assessment of Fluidic Oscillators Tested on the NASA Hump Model

Köklü

2021

Fluids

Self Cite

View full text Add to dashboard Cite

Flow separation control over a wall-mounted hump model was studied experimentally to assess the performance of fluidic oscillators (sweeping jet actuators). An array of fluidic oscillators was used to control flow separation. The results showed that the fluidic oscillators were able to achieve substantial control over the separated flow by increasing the upstream suction pressure and downstream pressure recovery. Using the data available in the literature, the performance of the fluidic oscillators was compared to other active flow control (AFC) methods such as steady blowing, steady suction, and zero-net-mass-flux (ZNMF) actuators. Several integral parameters, such as the inviscid flow comparison coefficient, pressure drag coefficient, and modified normal force coefficient, were used as quality metrics in the performance comparison of the AFC methods. These quality metrics indicated the superiority of the steady suction method, especially at lower excitation amplitudes that is followed by the fluidic oscillators, steady blowing, and the ZNMF actuators, respectively. An aerodynamic figure of merit (AFM) was also constructed using the integral parameters and AFC power usage. The AFM results revealed that, for this study, steady suction was the most efficient AFC method at lower excitation amplitudes. The steady suction loses its efficiency as the excitation amplitude increases, and the fluidic oscillators become the most efficient AFC method. Both the steady suction and the fluidic oscillators have an AFM > 1 for the range tested in this study, indicating that they provide a net benefit when the AFC power consumption is also considered. On the other hand, both the steady blowing and ZNMF actuators were found to be inefficient AFC methods (AFM < 1) for the current configuration. Although they improved the flow field by controlling flow separation, the power requirement was more than their benefit.

show abstract

Section: Performance Assessment Of Fluidic Oscillatorsmentioning

confidence: 99%

Performance Assessment of Fluidic Oscillators Tested on the NASA Hump Model

Köklü

2021

Fluids

Self Cite

View full text Add to dashboard Cite

show abstract

“…One viable option is to use simplified high-lift (SHL) systems with simple-hinged flaps [1]. The simple-hinged flaps are the simplest and the most basic flaps for high-lift systems; however, they are vulnerable to flow separation that is detrimental to the aerodynamic performance during takeoff and landing operations [1][2][3][4]. The SHL systems are capable of attaining the required aerodynamic performance only if the flow separation over the flap is controlled, for example, using an active flow control (AFC) system.…”

Section: Nomenclaturementioning

confidence: 99%

Investigation of the Nacelle/Pylon Vortex System on the High-Lift Common Research Model

et al. 2021

Self Cite

View full text Add to dashboard Cite

A 10%-scale high-lift version of the Common Research Model (CRM-HL) was tested in the NASA Langley Research Center's 14 by 22 ft subsonic tunnel. The focus of the wind-tunnel tests was to investigate the vortices generated at the nacelle/pylon region and their effect on the aerodynamic performance. The wind-tunnel measurements included the acquisition of force and moment data, steady pressure data, as well as surface flow visualization using minitufts. For some select cases, numerical simulations were performed to aid in understanding the wind-tunnel data. Wind-tunnel tests, with and without the nacelle/pylon, indicated a lift degradation of the conventional CRM-HL at high angles of attack. The surface flow visualization with fluorescent minitufts revealed that the lift degradation is due to flow separation caused by the nacelle/pylon vortex system on the inboard wing. The consequent flow separation was successfully mitigated using a nacelle chine installed on the inboard side of the engine nacelle.

show abstract

“…[7]- [11]. A lift increment of 0.13 was obtained for a momentum coefficient C μ equal to 1% and a rudder deflection δ equal to 20°.…”

Section: Introductionmentioning

confidence: 99%

“…They concluded that the actuators act as fluidic boundary layer fences and that a limited number of actuators (two in this case) with a C μ of 1% were able to reach the same lift coefficient than twenty nine actuators with a C μ of 2%. Like Pack Melton et al [7]- [11], Krӧhnert [31] investigated numerically a simplified two-dimensional configuration. A lift increment of 0.8 was reached with a steady blowing slot with a C μ of 2.5%.…”

Section: Introductionmentioning

confidence: 99%

“…The present paper is composed of two parts. In the first part, in the same manner as in Pack Melton et al [7]- [11], AFC is studied experimentally on a two-dimensional configuration to prepare the wind tunnel tests on the 6 VTP. The novelty is that different types of actuation (continuous/pulsed blowing through slots, continuous blowing through segmented slots, sweeping jets) are compared in terms of efficiency on the same model.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Performance Enhancement of a Vertical Tail Model with Sweeping Jets

2020

View full text Add to dashboard Cite

Active flow control to delay the flow separation on the rudder of two different models has been investigated in the ONERA L1 wind tunnel. The first model was used as a simplified test case and consisted in a flat plate with a rudder. Different types of actuation were investigated: continuous/pulsed blowing through slots, continuous blowing through segmented slots and sweeping jets. The lift increments of these different types of actuation were compared not only in terms of mass flow rate but also in terms of momentum and power coefficients. Active flow control by sweeping jets was selected to be tested on the second model which is a scale 1:2 vertical tail model of a generic business jet. Side force increments up to 80% were achieved with a 2% value of C μ coefficient. Side force increments of 50% were also reached with a lower C μ value of 0.5%. These side force increments could lead to a reduction of vertical tail plane wetted area and weight and consequently to a reduction of drag cruise and fuel consumption.

show abstract

Active Flow Control via Discrete Sweeping and Steady Jets on a Simple-Hinged Flap

Cited by 33 publications

References 26 publications

Performance Assessment of Fluidic Oscillators Tested on the NASA Hump Model

Performance Assessment of Fluidic Oscillators Tested on the NASA Hump Model

Investigation of the Nacelle/Pylon Vortex System on the High-Lift Common Research Model

Performance Enhancement of a Vertical Tail Model with Sweeping Jets

Contact Info

Product

Resources

About