An Experimental Study of Dynamic Trailing Edge Deflections on a Two Dimensional Translating Wing

2013 ◽  
Author(s):  
Yun Liu ◽  
Bo Cheng ◽  
Xinyan Deng
Keyword(s):  
Experimental Study ◽  
Two Dimensional ◽  
Trailing Edge

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.

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

Theoretical and experimental study of fabrics developed by different shaped markers in two-dimensional simple shear

1983 ◽  
Vol S7-XXV (3) ◽  
pp. 319-326 ◽  
Author(s):  
Angel Fernandez ◽  
Jean-Louis Feybesse ◽  
Jean-Francois Mezure
Keyword(s):  
Experimental Study ◽  
Simple Shear ◽  
Two Dimensional

Turbulent-like velocity fluctuations in two-dimensional granular materials subject to cyclic shear

Soft Matter ◽  
2022 ◽  
Author(s):  
Aile Sun ◽  
Yinqiao Wang ◽  
Yangrui Chen ◽  
Jin Shang ◽  
Jie Zheng ◽  
...  
Keyword(s):  
Experimental Study ◽  
Granular Materials ◽  
Granular Matter ◽  
Two Dimensional ◽  
Friction Coefficients ◽  
Velocity Fluctuations ◽  
Cyclic Shear

We perform a systematic experimental study to investigate the velocity fluctuations in the two-dimensional granular matter of low and high friction coefficients subjected to cyclic shear of a range of...

scholarly journals Investigation of Flows in Rectangular Diffusers With Inlet Flow Distortion

1982 ◽  
Author(s):  
M. M. Al-Mudhafar ◽  
M. Ilyas ◽  
F. S. Bhinder
Keyword(s):  
Experimental Study ◽  
Velocity Profiles ◽  
Pressure Recovery ◽  
Two Dimensional ◽  
Flow Distortion ◽  
Inlet Flow ◽  
Inlet Velocity ◽  
Inlet Distortion ◽  
Mach Numbers ◽  
Inlet Flow Distortion

The results of an experimental study on the influence of severely distorted velocity profiles on the performance of a straight two-dimensional diffuser are reported. The data cover entry Mach numbers ranging from 0.1 to 0.6 and several inlet distortion levels. The pressure recovery progressively deteriorates as the inlet velocity is distorted.

Part II: Steady aerofoil-spoiler characteristics

1987 ◽  
Vol 91 (908) ◽  
pp. 359-366
Keyword(s):  
Separated Flow ◽  
Experimental Results ◽  
Surface Singularity ◽  
Separation Region ◽  
Two Dimensional ◽  
Trailing Edge ◽  
Singularity Method ◽  
Total Head ◽  
Low Speeds ◽  
Theoretical Results

Summary A surface singularity method has been formulated to predict two-dimensional spoiler characteristics at low speeds. Vorticity singularities are placed on the aerofoil surface, on the spoiler surface, on the upper separation streamline from the spoiler tip and on the lower separation streamline from the aerofoil trailing edge. The separation region is closed downstream by two discrete vortices. The flow inside the separation region is assumed to have uniform total head. The downstream extent of the separated wake is an empirical input. The flows both external and internal to the separated regions are solved. Theoretical results have been obtained for a range of spoiler-aerofoil configurations which compare reasonably with experimental results. The model is deficient in that it predicts a higher compression ahead of the spoiler than obtained in practice. Furthermore, there is a minimum spoiler angle below which a solution is not possible; it is thought that this feature is related to the physical observation that at small spoiler angles, the separated flow from the spoiler reattaches on the aerofoil upper surface ahead of the trailing edge.

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