Experimental investigation of a blunt trailing edge flow field with application to sound generation

2006 ◽  
Vol 41 (5) ◽  
pp. 777-788 ◽  
Author(s):  
Daniel W. Shannon ◽  
Scott C. Morris
Keyword(s):  
Experimental Investigation ◽  
Flow Field ◽  
Sound Generation ◽  
Trailing Edge ◽  
Blunt Trailing Edge ◽  
Edge Flow

Numerical and experimental investigation of a beveled trailing-edge flow field and noise emission

2016 ◽  
Vol 384 ◽  
pp. 113-129 ◽  
Author(s):  
W.C.P. van der Velden ◽  
S. Pröbsting ◽  
A.H. van Zuijlen ◽  
A.T. de Jong ◽  
Y. Guan ◽  
...  
Keyword(s):  
Experimental Investigation ◽  
Flow Field ◽  
Noise Emission ◽  
Trailing Edge ◽  
Beveled Trailing Edge ◽  
Edge Flow

Radiated sound and turbulent motions in a blunt trailing edge flow field

2006 ◽  
Vol 27 (4) ◽  
pp. 730-736 ◽  
Author(s):  
Daniel W. Shannon ◽  
Scott C. Morris ◽  
Thomas J. Mueller
Keyword(s):  
Flow Field ◽  
Trailing Edge ◽  
Blunt Trailing Edge ◽  
Radiated Sound ◽  
Edge Flow

Two-Dimensional Experimental Investigation on the Effects of a Fowler Flap Gap and Overlap Size on the Wake Flow Field

2016 ◽  
Vol 139 (2) ◽  
Author(s):  
David Demel ◽  
Mohsen Ferchichi ◽  
William D. E. Allan ◽  
Marouen Dghim
Keyword(s):  
Experimental Investigation ◽  
Flow Field ◽  
Angle Of Attack ◽  
Wake Flow ◽  
Two Dimensional ◽  
Edge Region ◽  
Suction Surface ◽  
Trailing Edge ◽  
Piv Measurements ◽  
Image Velocimetry

This work details an experimental investigation on the effects of the variation of flap gap and overlap sizes on the flow field in the wake of a wing-section equipped with a trailing edge Fowler flap. The airfoil was based on the NACA 0014-1.10 40/1.051 profile, and the flap was deployed with 40 deg deflection angle. Two-dimensional (2D) particle image velocimetry (PIV) measurements of the flow field in the vicinity of the main wing trailing edge and the flap region were performed for the optimal flap gap and overlap, as well as for flap gap and overlap increases of 2% and 4% chord beyond optimal, at angles of attack of 0 deg, 10 deg, and 12 deg. For all the configurations investigated, the flow over the flap was found to be fully stalled. At zero angle of attack, increasing the flap gap size was found to have minor effects on the flow field but increased flap overlap resulted in misalignment between the main wing boundary layer (BL) flow and the slot flow that forced the flow in the trailing edge region of the main wing to separate. When the angle of attack was increased to near stall conditions (at angle of attack of 12 deg), increasing the flap gap was found to energize and improve the flow in the trailing edge region of the main wing, whereas increased flap overlap further promoted flow separation on the main wing suction surface possibly steering the wing into stall.

Experimental Investigation of the Vortex Shedding in the Wake of Oblique and Blunt Trailing Edge Hydrofoils Using PIV-POD Method

2010 ◽  
Author(s):  
Amirreza Zobeiri ◽  
Philippe Ausoni ◽  
Franc¸ois Avellan ◽  
Mohamed Farhat
Keyword(s):  
Experimental Investigation ◽  
Phase Shift ◽  
Vortex Shedding ◽  
High Speed ◽  
Flow Induced Vibration ◽  
Trailing Edge ◽  
Blunt Trailing Edge ◽  
Vortex Induced Vibrations ◽  
Image Velocimetry ◽  
High Reynolds

This paper presents an experimental investigation of the vortex shedding in the wake of blunt and oblique trailing edge hydrofoils at high Reynolds number, Re = 5 105 − 2.9 106. The velocity field in the wake is surveyed with the help of Particle-Image-Velocimetry, PIV, using Proper-Orthogonal-Decomposition, POD. Besides, flow induced vibration measurements and high-speed visualization are performed. The high-speed visualization clearly shows that the oblique trailing edge leads to a spatial phase shift of the upper and lower vortices at their generation stage, resulting their partial cancellation. For the oblique trailing edge geometry and in comparison with the blunt one, the vortex-induced vibrations are significantly reduced. Moreover, PIV data reveals a lower vorticity for the oblique trailing edge. The phase shift between upper and lower vortices, introduced by the oblique truncation of the trailing edge, is found to vanish in the far wake, where alternate shedding is recovered as observed with the blunt trailing edge. The phase shift generated by the oblique trailing edge and the resulting partial cancellation of the vortices is believed to be the main reason of the vibration reduction.

Numerical and experimental investigation of a beveled trailing edge flow and noise field

2015 ◽  
Author(s):  
Wouter C. van der Velden ◽  
Stefan Pröbsting ◽  
Arjen de Jong ◽  
Alexander van Zuijlen ◽  
Yaoyi Guan ◽  
...  
Keyword(s):  
Experimental Investigation ◽  
Trailing Edge ◽  
Noise Field ◽  
Beveled Trailing Edge ◽  
Edge Flow

An Experimental Investigation of a Low-Speed Circulation-Controlled Aerofoil

1968 ◽  
Vol 19 (2) ◽  
pp. 170-182 ◽  
Author(s):  
R. J. Kind ◽  
D. J. Maull
Keyword(s):  
Experimental Investigation ◽  
Angle Of Incidence ◽  
Pitching Moment ◽  
Two Dimensional ◽  
Trailing Edge ◽  
Low Speed ◽  
Momentum Coefficient ◽  
Blunt Trailing Edge ◽  
Elliptic Section ◽  
Jet Blowing

SummaryExperiments performed on a low-speed circulation-controlled aerofoil are described. The aerofoil was of elliptic section with the circulation controlled by means of a jet blowing around the blunt trailing edge. Results for the lift, drag and pitching moment on the aerofoil are presented as functions of the blowing momentum coefficient and the angle of incidence. The results are for a two-dimensional aerofoil. Possible applications of this type of aerofoil are briefly discussed.

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