Experimental Evaluation of Sinusoidal Leading Edges

Miklosovic, David; Murray, Mark M.; Howle, Laurens E.

doi:10.2514/1.30303

Cited by 219 publications

(154 citation statements)

References 7 publications

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“…Further studies on modified two-dimensional airfoils at low Reynolds number show that, similar to three-dimensional ones, the lift gradually drops at stall angles while it still stays greater than that of the unmodified models at the post-stall angle. On the other hand, the pre-stall performance suffers from the appearance of the leading edge tubercles (Stein and Murray, 2005;Johari et al, 2007;Hansen et al, 2011;Miklosovic et al, 2007). Cranston et al (2012) fabricated flat plates with saw-tooth serrations on the leading edge to examine the effect of the leading edge variation on the aerodynamic performance in absence of the curvature and thickness change effects.…”

Section: Introductionmentioning

confidence: 99%

Streamwise counter-rotating vortices generated by triangular leading edge pattern in flat plate boundary layer

Hasheminejad

Mitsudharmadi

Winoto

et al. 2016

J Vis

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A series of flow visualizations were conducted to qualitatively study the development of streamwise counter-rotating vortices over a flat plate induced by triangular patterns at the leading edge of a flat plate. The experiments were carried out for a Reynolds number based on the pattern wavelength (λ) of 3080. The results depict the onset, development and breakdown of the vortical structures within the flat plate boundary layer. Moreover, the effect of one spanwise array of holes with diameter of 0.2λ (=3 mm) was examined. This investigation was done on two different flat plates with holes placed at the location x/λ=2 downstream of the troughs and peaks. The presence of holes after troughs does not show any significant effect on the vortical structures. However, the plate with holes after peaks noticeably delays the vortex breakdown. In this case, the "mushroom-like" vortices move away from the wall and propagate downstream with stable vortical structures. The vortex growth is halted further downstream but start to tilt aside.

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Section: Introductionmentioning

confidence: 99%

Streamwise counter-rotating vortices generated by triangular leading edge pattern in flat plate boundary layer

Hasheminejad

Mitsudharmadi

Winoto

et al. 2016

J Vis

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“…They demonstrated experimentally that the angle of attack at which stall occurred was significantly delayed when leading edge serrations were introduced onto a model whale flipper geometry. Miklosovic et al (2007) performed the aerodynamic evaluation on a full-scale humpback whale flipper geometry to simulate the effects of LE tubercles. They demonstrated experimentally that serrations on the aerofoil leading edge produced vortices from the serration peaks which significantly altered the performance of the serrated aerofoil.…”

Section: Introductionmentioning

confidence: 99%

Aerofoil geometry effects on turbulence interaction noise

Paruchuri

2015

21st AIAA/CEAS Aeroacoustics Conference

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Faculty of Engineering and the Environment Institute of Sound and Vibration Research Doctor of PhilosophyAerofoil geometry effects on turbulence interaction noise by Chaitanya PARUCHURI Fan broadband is one of the dominant noise sources on an aircraft engine, particularly at approach. The dominant noise generation mechanism is due to turbulent-aerofoil interaction noise (TAI). This thesis investigates the effect of changes in 2D aerofoil geometry on TAI noise. The main focus of this thesis is to attempt to reduce it through the development of innovative leading edge geometries. The first two chapters of the thesis deals with an experimental and numerical investigation into the effect of aerofoil geometry on interaction noise on single aerofoils and on cascades. Consistent with previous work, they show that variations in aerofoil parameters, such as aerofoil thickness, leading edge nose radius and camber, produce only a small changes in broadband interaction noise at approach conditions. Subsequent chapters deal with the development of innovative leading edge serration profiles aimed at reducing interaction noise. Chapter 4 is a detailed study into the limitations of single-wavelength serrations in reducing interaction noise. The optimum profile is identified. Chapters 5, 6 and 7 all deal with the development of innovative profiles that can provide up to 10dB of additional noise reductions compared to single-wavelength serrations. For each of the profiles investigated a simple model is developed to aid the understanding of their interaction mechanism. v

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“…Their study considered humpback whale flipper models in a wind tunnel. Subsequently, Miklosovic et al [4] investigated the performance on two-dimensional wings with a wavy leading edge in a wind tunnel. They reported that the effects of wavy leading edge are different between on the humpback whale flipper models and two-dimensional wings.…”

Section: Introductionmentioning

confidence: 99%

A Study on Stall Delay by Various Wavy Leading Edges

et al. 2010

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Abstract-The objective of the present study is to elucidate the flow mechanism of delaying stall by use of a wavy leading edge. Experiments were carried out to examine the effects of various shapes of wavy leading edges. Numerical simulations were also carried out to investigate the flow around wavy leading edge. It is found that the wavy leading edge can restrain flow separation and delay stall. The shorter wavelength of protuberance is the better for producing large lift force at poststall angles of attack on rectangular wing.

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Experimental Evaluation of Sinusoidal Leading Edges

Cited by 219 publications

References 7 publications

Streamwise counter-rotating vortices generated by triangular leading edge pattern in flat plate boundary layer

Streamwise counter-rotating vortices generated by triangular leading edge pattern in flat plate boundary layer

Aerofoil geometry effects on turbulence interaction noise

A Study on Stall Delay by Various Wavy Leading Edges

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