Measurements of Midspan Flow Interactions of a Low-Aspect-Ratio Circulation Control Wing

Miklosovic, David; Imber, Robin; Britt-Crane, Michael

doi:10.2514/1.c033852

Cited by 9 publications

(3 citation statements)

References 11 publications

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“…At t * g = 0 , the wake profile is deflected downwards and the effect of the upper jet is directly visible as added velocity in the velocity distribution in the form of a plateau around z∕c ≈ 0.007 . This secondary peak is due to the separated jet entering the wake, as also shown in Miklosovic et al (2016). As the lower jet builds Fig.…”

Section: Jet Performance For Impulsive Activationmentioning

confidence: 70%

“…Based on available literature, a linear lift change is expected with increasing c for small values of c , in the socalled boundary layer control region (Englar and Williams 1971;Abramson 1975;Alexander et al 2005). For larger blowing rates, in the so-called circulation region, a square root dependency is found that converges asymptotically against a limit that corresponds to the condition where the jet is fully wrapped around the Coandă surface (Miklosovic et al 2016). For this reason, the Coandă actuator exhibits the best lift gain factor Δc L ∕c in the boundary layer control region, i.e.…”

Section: Introductionmentioning

confidence: 94%

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Experimental load modification on a dual-slot circulation control airfoil

2022

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Active load alleviation can substantially contribute to decrease structural weight and emissions of future transport aircraft by limiting peak aerodynamic loads that the aircraft experiences during flight. Fluidic actuators, as part of active load alleviation systems, have the potential for faster and more complete gust load reduction. The performance of a dual slot circulation control airfoil for gust load alleviation is investigated experimentally on a supercritical airfoil model. The tests are conducted in a low-speed wind tunnel at a chord-based Reynolds number of $${\text{Re}}={\text{1.5}}\cdot {\text{10}}^{{\text{6}}}$$ Re = 1.5 · 10 6 and $${\it{M}}_{{\infty }}={\text {0.14}}$$ M ∞ = 0.14 . The model features an elliptical Coandă geometry integrated into the airfoil’s trailing edge to minimize cruise performance penalty, while still allowing for substantial load reduction. Blowing from a single slot, as well as simultaneously from pressure and suction side slots is tested over a range of blowing rates to assess the impact on load modification. Both steady and impulsive activation performance are evaluated based on surface pressure, integral load, and flow field measurements around the Coandă geometry. High control authority is found for upper and lower single slot blowing, with peak changes in lift coefficient of about $$\pm\,{0.33}$$ ± 0.33 and lift-to-equivalent-drag ratio change of up to 100. Similar peak lift changes and reduced equivalent drag are obtained by adding marginal ($$< 14\%$$ < 14 % of total) blowing from the opposite slot, which also reduces pitching moment changes for primary upper and marginal lower blowing. Impulsive jet activation exhibits load control authority comparable to steady actuation and sufficiently short onset times to counteract all gusts defined by certification documentation.

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Section: Jet Performance For Impulsive Activationmentioning

confidence: 70%

Section: Introductionmentioning

confidence: 94%

Experimental load modification on a dual-slot circulation control airfoil

2022

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“…Controlling flow attachment on aerodynamic surfaces is one of the main engineering subjects of recent years. From aircraft wings [1] or thrust vectoring [2] to both radial [3] or axial [4] flow turbomachinery and even synthetic jets in sports vehicles [5] and buildings [6], having the ability to control boundary layer separation opens new possibilities for design and operation. This paper deals with a theoretical concept for flow control which has been tested, using state of the art CFD methods, with advanced turbulence modeling.…”

Section: Introductionmentioning

confidence: 99%

A Numerical Proof of Concept for Thermal Flow Control

Drãgan

2017

Eng. Technol. Appl. Sci. Res.

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In this paper computational fluid dynamics is used to provide a proof of concept for controlled flow separation using thermal wall interactions with the velocity boundary layer. A 3D case study is presented, using a transition modeling Shear Stress Transport turbulence model. The highly loaded single slot flap airfoil was chosen to be representative for a light aircraft and the flow conditions were modeled after a typical landing speed. In the baseline case, adiabatic walls were considered while in the separation control case, the top surface of the flaps was heated to 500 K. This heating lead to flow separation on the flaps and a significant alteration of the flow pattern across all the elements of the wing. The findings indicate that this control method has potential, with implications in both aeronautical as well as sports and civil engineering applications.

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Circulation-controlled wind-assisted ship propulsion: Technical innovations for future shipping industry decarbonization

Li,

Tang

2024

Energy Conversion and Management

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Measurements of Midspan Flow Interactions of a Low-Aspect-Ratio Circulation Control Wing

Cited by 9 publications

References 11 publications

Experimental load modification on a dual-slot circulation control airfoil

Experimental load modification on a dual-slot circulation control airfoil

A Numerical Proof of Concept for Thermal Flow Control

Circulation-controlled wind-assisted ship propulsion: Technical innovations for future shipping industry decarbonization

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