Experimental Study of Circulation Control Wings at Low Reynolds Numbers

Kanistras, Konstantinos; Rutherford, Matthew J.; Vitzilaios, Nikolaos; Valavanis, Kimon P.

doi:10.2514/6.2014-2307

Cited by 11 publications

(4 citation statements)

References 5 publications

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“…The numerical results were compared to the existing experimental results obtained by Lockheed Georgia in 1986. The velocity of the oncoming flow is 42.5 m/s and the Reynolds number based on the aerofoil chord length is 1×10 6 in their experiments. The geometry of the aerofoil profile and jet orifice can be found in Ref.…”

Section: Numerical Methods and Cfd Validationmentioning

confidence: 98%

“…The results showed that it has the potential of controlling the tip vortex and reducing the blade/vortex interaction noise. In order to find the structure providing the largest lift augmentation, Kanistras et al (6) tested three circulation control wings (S8036 aerofoil, NACA0015 aerofoil, and NACA2412 aerofoil) in a low-speed wind tunnel. The circulation control aerofoils are also proved to be efficient under high-speed conditions (7,8) .…”

Section: Introductionmentioning

confidence: 99%

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Numerical simulation of circulation control turbine cascade with Coanda jet and counter-flow blowing at high Mach numbers

2017

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The performance of a circulation-control inlet guide vane that makes use of the Coanda effect was studied numerically in a high Mach number turbine cascade. The effect of different shapes (elliptic and circular) of the Coanda surface at the blade trailing edge was investigated by implementing both a Coanda jet and a counter-flow blowing. Under high subsonic flow conditions, with a total blowing ratio of 3% of the mainstream, the circulation control cascade can reach the same performance as the reference stator with a 13.5% reduction in the axial chord length, with minimal increase of the energy loss coefficient. The Coanda surfaces with small curvature are more efficient in entraining the mainstream flow, and they achieve better aerodynamic performance. The wall attachment of the Coanda jet is improved by employing counter-flow blowing, resulting in a slight increase of both the exit flow angle and the expansion ratio. Under supersonic flow conditions at the cascade exit, it is more difficult for the circulation control cascade to reach the appropriate flow turning due to a premature shock wave, which is absent in the original cascade until the very end of the suction surface.

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Section: Numerical Methods and Cfd Validationmentioning

confidence: 98%

Section: Introductionmentioning

confidence: 99%

Numerical simulation of circulation control turbine cascade with Coanda jet and counter-flow blowing at high Mach numbers

2017

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“…The selection of the airfoil profile NACA 0015, which is a symmetrical airfoil with a 15% thickness, is largely driven by the good CCW characteristics for upper slot TE blowing cases. 10,11 It gives the highest lift enhancement compared to other airfoils and high augmentation ratios with the 2:1 Coanda surface configuration. The wing model is rapid prototyped out of acrylonitrile-butadiene-styrene (ABS) plastic and the surface is covered with tape to give a smoother finish.…”

Section: Wing Designmentioning

confidence: 93%

“…Due to the fixed-wing geometry and design restrictions (plenum design and compressed air supply) an external force balance configuration is chosen. Details of the design and the calibration process that is followed can be found in Kanistras et al 10 …”

Section: Force Balancementioning

confidence: 99%

Low Speed Wind Tunnel Investigation of a Circulation Control Wing for Enhanced Lift

Kanistras

Saka

Valavanis

et al. 2015

33rd AIAA Applied Aerodynamics Conference

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The objective of this research is to investigate the efficacy of Circulation Control (CC) at low Reynolds numbers (Re=150,000) with relatively low blowing rates on a modified NACA0015 wing. Two dual radius flap geometries are developed and tested by varying specific flap parameters from a previously studied baseline configuration. A two-dimensional (2-D) low-speed wind-tunnel experimental study is undertaken to evaluate the effect of trailing edge upper slot blowing at cruise flight, takeoff and landing (0 o , 30 o and 60 o flap deflection). The wind tunnel tests are conducted at Mach numbers of 0.03, with momentum coefficients of blowing (Cµ) ranging from 0.0 to 0.3. It is found that CC blowing is effective at all cases enabling the wing to achieve high lift-to-drag ratios and high lift augmentation during takeoff and landing. The modified NACA0015 with the smaller Coanda radius ratio (r2/r1) flap is found to be the most efficient at CC blowing achieving a maximum incremental lift coefficient (∆C l ) of 0.89 at 30 0 flap deflection. The lift-to-drag ratio is increased up to 11 times at δ f = 0 o flap deflection and α = 0 o using the same flap configuration.

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