Parametric Investigation of a High-Lift Airfoil at High Reynolds Numbers

Lin, John C.; Dominik, Chet J.

doi:10.2514/2.2217

Cited by 44 publications

(12 citation statements)

References 4 publications

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“…4 However, a comparison at the same Re c can be made based on data from the current research effort. Figure 6 compares the lift values at Re c = 2.5×10 6 and Re c = 9×10 6 .…”

Section: Cruise and High-lift Baseline Airfoil Performancementioning

confidence: 99%

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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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“…4 However, a comparison at the same Re c can be made based on data from the current research effort. Figure 6 compares the lift values at Re c = 2.5×10 6 and Re c = 9×10 6 .…”

Section: Cruise and High-lift Baseline Airfoil Performancementioning

confidence: 99%

“…4 It is the goal of the current research effort to achieve similar performance with a single-element simplified high-lift system augmented with active flow control. Prior to describing the present experiment and presenting the results some background information is provided.…”

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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show abstract

“…Fig. 44 depicts a multi-element airfoil in the test section [109]. The model is mounted horizontally and the photo clearly depicts the sizeable brackets required to support the slat and the flap at the high dynamic pressure conditions encountered in pressurized tunnels.…”

Section: Wind-tunnel Testingmentioning

confidence: 99%

The aerodynamic design of multi-element high-lift systems for transport airplanes

Dam¹

2002

Progress in Aerospace Sciences

254

109

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High-lift systems have a major influence on the sizing, economics, and safety of most transport airplane configurations. The combination of complexity in flow physics, geometry, and system support and actuation has historically led to a lengthy and experiment intensive development process. However, during the recent past engineering design has changed significantly as a result of rapid developments in computational hardware and software. In aerodynamic design, computational methods are slowly superseding empirical methods and design engineers are spending more and more time applying computational tools instead of conducting physical experiments to design and analyze aircraft including their high-lift systems. The purpose of this paper is to review recent developments in aerodynamic design and analysis methods for multi-element high-lift systems on transport airplanes. Attention is also paid to the associated mechanical and cost problems since a multi-element high-lift system must be as simple and economical as possible while meeting the required aerodynamic performance levels. r

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“…The simplified high-lift version of the NASA EET (Energy Efficient Transport) airfoil model [14] was designed in a modular manner so that zero-net-mass-flux actuators could replace solid regions in the model near the leading and trailing edge flap shoulders (Fig. 1a).…”

Section: Simplified High-lift Modelmentioning

confidence: 99%

Control and Identification of Turbulent Boundary Layer Separation

Seifert

Melton

2006

Solid Mechanics and Its Applications

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Abstract:Effective delay of turbulent boundary layer separation could be achieved via closed-loop control. Constructing such a system requires that sensor data be processed, real-time, and fed into the controller to determine the output. Current methods for detection of turbulent boundary layer separation are lacking the capability of localized, fast and reliable identification of the boundary layer state. A method is proposed for short-time FFT processing of time series, measured by hot-film sensors, with the purpose of identifying the alternation of the balance between small and large scales as the boundary layer separates, favoring the large scales. The method has been validated by comparison to other criteria of separation detection and over a range of baseline and controlled flow conditions on a "simplified" high-lift system, incorporating active flow control.

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Parametric Investigation of a High-Lift Airfoil at High Reynolds Numbers

Abstract: A new two-dimensional, three-element, advanced high-lift research airfoil has been tested in

Cited by 44 publications

References 4 publications

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

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

The aerodynamic design of multi-element high-lift systems for transport airplanes

Control and Identification of Turbulent Boundary Layer Separation

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