Numerical and Experimental Study of Flow Around Two Plates Having Asymmetric Beveled Trailing Edge

2008 ◽  
Vol 20 (5) ◽  
pp. 624-628
Author(s):  
M. M. Mosallem
Keyword(s):  
Experimental Study ◽  
Trailing Edge ◽  
Beveled Trailing Edge

Experimental study of a cooling scheme for a turbine blade trailing edge

2015 ◽  
Vol 229 (8) ◽  
pp. 832-848 ◽  
Author(s):  
Ahmed Beniaiche ◽  
Adel Ghenaiet ◽  
Carlo Carcasci ◽  
Marco Pievarolli ◽  
Bruno Facchini
Keyword(s):  
Experimental Study ◽  
Turbine Blade ◽  
Trailing Edge

Experimental study of wavy trailing edge serrations on flat rotor blades

2021 ◽  
Vol 263 (5) ◽  
pp. 1855-1866
Author(s):  
Sai Manikanta Kaja ◽  
K. Sriinivasan ◽  
A. Jaswanth Kalyan Kumar
Keyword(s):  
Experimental Study ◽  
Noise Reduction ◽  
Pitch Angle ◽  
Acoustic Emissions ◽  
Broadband Noise ◽  
Rotor Blades ◽  
Tonal Noise ◽  
Trailing Edge ◽  
Low Speeds ◽  
Trailing Edge Serrations

A detailed experimental study is conducted to observe the effect of various parameters like wavelength, depth of serrations, and pitch angle on serrated blades' acoustic emissions at low speeds up to 2000 rpm. Experiments are conducted on flat blade rotors with sinusoidal serrations on the trailing edge of blades with different amplitudes and wavelengths. A total of 7 blades with different serration configurations, including a base configuration, are studied, five of them have serrations throughout the span of the blade, and one configuration has serration of varying amplitude on the farther half of the blade. It is observed that some blade configurations have resulted in tonal noise reduction noise as much as 8dB, whereas some of the serration configurations reduce very little to none, there is no significant effect of T.E serrations on the broadband noise emitted by the rotor. Directivity of noise generated from the rotor, the effect of serrations on the directivity of the noise is studied.

An experimental study of a trailing vortex alleviation using an undulated trailing edge

2021 ◽  
Author(s):  
Rolando Cruz Marquez ◽  
Jean Claude Monnier ◽  
Geoffrey Tanguy ◽  
Marie Couliou ◽  
Vincent Brion ◽  
...  
Keyword(s):  
Experimental Study ◽  
Trailing Edge

An experimental study of trailing edge noise from a heaving airfoil

2020 ◽  
Vol 147 (6) ◽  
pp. 4020-4031
Author(s):  
Teng Zhou ◽  
Xin Zhang ◽  
Siyang Zhong
Keyword(s):  
Experimental Study ◽  
Trailing Edge ◽  
Trailing Edge Noise

Surface pressures and their corrections for the flow past a finite-length plate in supersonic low density flow

1979 ◽  
Vol 95 (1) ◽  
pp. 177-187 ◽  
Author(s):  
S. L. Gai
Keyword(s):  
Experimental Study ◽  
Finite Length ◽  
Leading Edge ◽  
Low Density ◽  
Cold Wall ◽  
Trailing Edge ◽  
Flow Past ◽  
Density Flow ◽  
Recent Method

An experimental study of the flow past a thin finite length plate in a supersonic low density stream is reported. The paper discusses the corrections that are necessary for surface pressures measured under rarefied conditions. It is shown that the recent method of ‘orifice’ corrections due to Harbour & Bienkowski is versatile and reliable to use for both cold wall and insulated wall measurements. For the conditions of the experiment, the flow over the plate was found to be dominated by both leading-edge and trailing-edge interactions.

An Experimental Study of Rectilinear Jet-Flap Cascades

1972 ◽  
Vol 94 (1) ◽  
pp. 97-104 ◽  
Author(s):  
T. J. Landsberg ◽  
E. Krasnoff
Keyword(s):  
Experimental Study ◽  
Momentum Flux ◽  
Two Dimensional ◽  
Trailing Edge ◽  
Tangential Blowing ◽  
Theoretical Results ◽  
Good Agreement

The performance of two-dimensional jet-flap cascades is determined experimentally. Stream deflection angles are presented as a function of the ratio of jet to mainstream momentum flux at chord spacing ratios of 0.375 and 0.75. Results obtained with conventional jet-flap airfoils (normal blowing near trailing edge) are in good agreement with published theoretical results. Tangential blowing jet-flap airfoils (tangential blowing over a rounded trailing edge) are shown to approximately double the turning effectiveness of the cascade.

scholarly journals Aerodynamic Performance of the Inboard Elevon on a Blendedwing- Body Aircraf

2021 ◽  
Author(s):  
Alexander Gordon Jackson
Keyword(s):  
Computational Model ◽  
Numerical Solutions ◽  
Aerodynamic Performance ◽  
Aerodynamic Design ◽  
Trailing Edge ◽  
Negative Deflection ◽  
Average Change ◽  
Implicit Solver ◽  
Blended Wing Body ◽  
Beveled Trailing Edge

The objectives of this research are to examine the effects of trailing edge modifications of the inboard elevon of a blended-wing-body (BWB) aircraft, the goal being to try and reduce the hinge moment of the inboard elevon through selective aerodynamic design. A computational model was built for 60⁰ and 70⁰ beveled trailing edge modifications, as well as no modification. The inboard elevon was deflected positive 5⁰ and negative 5⁰. The numerical solutions were obtained using an implicit solver and inviscid model. The results of this research showed that, through the use of a beveled trailing edge on the inboard elevon, a maximum of 112% reduction in the hinge moment could be achieved for the negative deflection case and a maximum of 88% reduction in the hinge moment for the positive deflection case. The results showed that there was a significant improvement in the hinge moments, with less that a 2% average change in the overall aerodynamic performance of the BWB for the inviscid models.

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