Active Control of Flow Separation from Supercritical Airfoil Leading-Edge Flap Shoulder

Melton, LaTunia Pack; Schaeffler, Norman W.; Yao, Chung-Sheng; Seifert, Avi

doi:10.2514/1.10294

Cited by 38 publications

(19 citation statements)

References 12 publications

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“…23 The OSU version requires a boundary layer trip to perform in a similar fashion. The focus of this work is on controlling separation at high α.…”

Section: A Airfoil Characterizationmentioning

confidence: 99%

“…Frequency sweeps using ΔC P at x/c=0.05 as a metric are presented at Re=0.75 x 10 6 and 1 x 10 6 in Figure 15b. 23 but the OSU version requires a boundary layer trip to perform in this fashion (see Figure 11). The data corresponding to this case (α=12 o ) in Figure 15 show no frequency preference in that once a threshold level is reached, control authority remains relatively constant.…”

Section: B Separation Controlmentioning

confidence: 99%

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Separation Control with Nanosecond-Pulse-Driven Dielectric Barrier Discharge Plasma Actuators

et al. 2012

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“…23 The OSU version requires a boundary layer trip to perform in a similar fashion. The focus of this work is on controlling separation at high α.…”

Section: A Airfoil Characterizationmentioning

confidence: 99%

Section: B Separation Controlmentioning

confidence: 99%

Separation Control with Nanosecond-Pulse-Driven Dielectric Barrier Discharge Plasma Actuators

et al. 2012

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“…Low Reynolds number results of Melton et al 1,2,3 showed that periodic excitation was effective at controlling leading-edge flap shoulder separation, increasing the maximum lift coefficient, C L,max , by 10-15% at low (less than 5…”

mentioning

confidence: 99%

High-Lift System for a Supercritical Airfoil: Simplified by Active Flow Control

Melton

Schaeffler

Lin

2007

45th AIAA Aerospace Sciences Meeting and Exhibit

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Active flow control wind tunnel experiments were conducted in the NASA Langley LowTurbulence Pressure Tunnel using a two-dimensional supercritical high-lift airfoil with a 15% chord hinged leading-edge flap and a 25% chord hinged trailing-edge flap. This paper focuses on the application of zero-net-mass-flux periodic excitation near the airfoil trailingedge flap shoulder at a Mach number of 0.1 and chord Reynolds numbers of 1.2×106 to 9×106 with leading-and trailing-edge flap deflections of -25• and 30• , respectively. The purpose of the investigation was to increase the zero-net-mass-flux options for controlling trailing edge flap separation by using a larger model than used on the low Reynolds number version of this model and to investigate the effect of flow control at higher Reynolds numbers. Static and dynamic surface pressures and wake pressures were acquired to determine the effects of flow control on airfoil performance. Active flow control was applied both upstream of the trailing edge flap and immediately downstream of the trailing edge flap shoulder and the effects of Reynolds number, excitation frequency and amplitude are presented. The excitations around the trailing edge flap are then combined to control trailing edge flap separation. The combination of two closely spaced actuators around the trailing-edge flap knee was shown to increase the lift produced by an individual actuator. The phase sensitivity between two closely spaced actuators seen at low Reynolds number is confirmed at higher Reynolds numbers. The momentum input required to completely control flow separation on the configuration was larger than that available from the actuators used.

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“…These vortices facilitate the transfer of momentum between the freestream and separated regions, consequently reattaching the flow to the body surface in the mean flow (Darabi et al 2004, Melton et al 2005. These vortices may couple with other instabilities downstream (separation bubbles, wakes, etc.)…”

Section: Leading Edge Airfoil Separation Controlmentioning

confidence: 99%

Control of Boundary Layer Separation and the Wake of an Airfoil using ns-DBD Plasma Actuators

Ashcraft

2016

54th AIAA Aerospace Sciences Meeting

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Active Control of Flow Separation from Supercritical Airfoil Leading-Edge Flap Shoulder

Cited by 38 publications

References 12 publications

Separation Control with Nanosecond-Pulse-Driven Dielectric Barrier Discharge Plasma Actuators

Separation Control with Nanosecond-Pulse-Driven Dielectric Barrier Discharge Plasma Actuators

High-Lift System for a Supercritical Airfoil: Simplified by Active Flow Control

Control of Boundary Layer Separation and the Wake of an Airfoil using ns-DBD Plasma Actuators

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