Advances in Planar Doppler Velocimetry for Large-Scale Wind Tunnels

2004 ◽  
Author(s):  
Robert McKenzie ◽  
Michael Reinath ◽  
Thomas Jenkins
Keyword(s):  
Large Scale ◽  
Wind Tunnels ◽  
Doppler Velocimetry

Planar Doppler velocimetry in a large-scale facility

AIAA Journal ◽  
2000 ◽  
Vol 38 ◽  
pp. 1010-1024 ◽  
Author(s):  
A. D. Mosedale ◽  
G. S. Elliott ◽  
C. D. Carter ◽  
T. J. Beutner
Keyword(s):  
Large Scale ◽  
Doppler Velocimetry

scholarly journals HFSB-seeding for large-scale tomographic PIV in wind tunnels

2016 ◽  
Vol 57 (12) ◽  
Author(s):  
Giuseppe Carlo Alp Caridi ◽  
Daniele Ragni ◽  
Andrea Sciacchitano ◽  
Fulvio Scarano
Keyword(s):  
Large Scale ◽  
Wind Tunnels ◽  
Tomographic Piv

Some specific features of atmospheric tubulence

1962 ◽  
Vol 13 (1) ◽  
pp. 77-81 ◽  
Author(s):  
A. M. Oboukhov
Keyword(s):  
Atmospheric Turbulence ◽  
Large Scale ◽  
Three Dimensional ◽  
Wind Tunnels ◽  
Small Scale ◽  
Horizontal Scale ◽  
Rough Approximation ◽  
External Conditions ◽  
Scale Turbulence

The spectrum of atmospheric turbulence is very broad by comparison with spectra in wind tunnels. We introduce the notion of small-scale and large-scale turbulence. Small-scale turbulence consists of a set of disturbances, the scales of which do not exceed the distance to the wall and for which the hypothesis of three-dimensional isotropy is valid in a certain rough approximation. Large-scale turbulence is essentially anisotropic; the horizontal scale in the atmosphere is much larger than the vertical one, the latter being confined to a certain characteristic height H. The horizontal scale varies widely according to the external conditions and characteristics of the medium.

scholarly journals Assessing the infinitely expanding intersection region for the development of large-scale multipoint laser Doppler velocimetry

2019 ◽  
Vol 70 ◽  
pp. 101660 ◽  
Author(s):  
Tomoaki Kyoden ◽  
Shunsuke Akiguchi ◽  
Tomoki Tajiri ◽  
Tsugunobu Andoh ◽  
Noriyuki Furuichi ◽  
...  
Keyword(s):  
Laser Doppler Velocimetry ◽  
Large Scale ◽  
Laser Doppler ◽  
Doppler Velocimetry

Boundary Layer and Loss Measurements on the Rotor of an Axial-Flow Turbine

1984 ◽  
Vol 106 (2) ◽  
pp. 391-399 ◽  
Author(s):  
H. P. Hodson
Keyword(s):  
Boundary Layers ◽  
Large Scale ◽  
Axial Flow ◽  
Turbine Rotor ◽  
Wind Tunnels ◽  
Shear Stresses ◽  
Surface Shear ◽  
Laminar Boundary Layers ◽  
Rotor Stator Interaction ◽  
Profile Loss

The aerodynamic efficiency of an axial-flow turbine is significantly less than that predicted by measurements made on equivalent cascades which operate with steady inflow. This difference in efficiencies is strongly dependent upon the rotor-stator axial spacing. An experimental investigation of the rotor-stator interaction has therefore been conducted using a large-scale, low-speed turbine. The blade profile loss and surface shear stresses are presented for the midspan of the rotor and for a rectilinear cascade of identical geometry. Both wind tunnels were operated at a Reynolds number of 3.15 × 105. The turbine rotor midspan profile loss was approximately 50 percent higher than that of the rectilinear cascade. The shear stress measurements indicate that as a stator wake is connected through a rotor passage, the laminar boundary layers undergo transition in the vicinity of the wake. The 50 percent increase in loss is due to the time-dependent transitional nature of the boundary layers.

Aircraft Research Association Limited

1966 ◽  
Vol 70 (661) ◽  
pp. 101-102
Author(s):  
R. Hills ◽  
E. J. Macadam
Keyword(s):  
Great Britain ◽  
Wind Tunnel ◽  
Large Scale ◽  
Second World War ◽  
Wind Tunnels ◽  
Research Association ◽  
World War ◽  
High Speeds ◽  
Second World

In the Years immediately following the Second World War, it became apparent that there was a lack of suitable wind tunnels in Great Britain to provide aerodynamic data at high speeds to meet all the needs of aircraft designers. The main firms had always had their own tunnels, but these were restricted in number and size because of the expense involved. Long-term research was carried out at the Royal Aircraft Establishment at Farnborough, but there was a need for a large-scale wind tunnel for more immediate development tests and especially for testing at transonic speeds.

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