Acoustic performance of the 40- by 80- foot wind tunnel test section deep acoustic lining

2000 ◽  
Author(s):  
Paul Soderman ◽  
Stephen Jaeger ◽  
Julie Hayes ◽  
Christopher Allen
Keyword(s):  
Wind Tunnel ◽  
Test Section ◽  
Wind Tunnel Test ◽  
Acoustic Performance ◽  
Acoustic Lining

Design of a deep acoustic lining for the 40- by 80-foot Wind Tunnel test section

1999 ◽  
Author(s):  
Paul Soderman ◽  
Fredric Schmitz ◽  
Christopher Allen ◽  
Stephen Jaeger ◽  
Joe Sacco ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Test Section ◽  
Wind Tunnel Test ◽  
Acoustic Lining

Suppression of background noise in a transonic wind-tunnel test section

AIAA Journal ◽  
1975 ◽  
Vol 13 (11) ◽  
pp. 1467-1471 ◽  
Author(s):  
L. A. Schutzenhofer ◽  
P. W. Howard
Keyword(s):  
Wind Tunnel ◽  
Test Section ◽  
Background Noise ◽  
Wind Tunnel Test ◽  
Transonic Wind Tunnel

Design of a Wind Tunnel Test Section for Single Airfoil Configuration With Real-Time Lift Force Control

2017 ◽  
Author(s):  
Aline Aguiar da Franca ◽  
Dirk Abel
Keyword(s):  
Wind Tunnel ◽  
Wind Turbine ◽  
Real Time ◽  
Force Control ◽  
Test Section ◽  
Lift Force ◽  
Angle Of Attack ◽  
Wind Tunnel Test ◽  
Wiener Model ◽  
Dynamic Matrix

This article presents a concept of test section for a closed-return wind tunnel, where the lift force of an airfoil, which depends on the angle of attack, is controlled in real-time. This airfoil is used to represent a wind turbine blade. The lift force of the blades is what produces the rotor torque of the wind turbine. This torque determines the amount of energy that will be captured by the wind turbine. The linear dynamics of the motor used to change the angle of attack and the static non-linearity of the airfoil are modeled as a Wiener model. The Quadratic Dynamic Matrix Controller based on Wiener model with linearizing pre-compensation is implemented to keep the lift force constant, which is desirable to avoid mechanical loads for wind turbine applications.

Flow Characterization of the NASA Langley Unitary Plan Wind Tunnel, Test Section 2: Computational Results

2021 ◽  
Author(s):  
Robert Childs ◽  
Paul Stremel ◽  
Veronica Hawke ◽  
Joseph Garcia ◽  
William L. Kleb ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Test Section ◽  
Wind Tunnel Test ◽  
Computational Results ◽  
Flow Characterization

scholarly journals Validation of a laminar-turbulent transition prediction technique for a swept-wing boundary-layer flow

2021 ◽  
Vol 2057 (1) ◽  
pp. 012081
Author(s):  
A V Boiko ◽  
V I Borodulin ◽  
A V Ivanov ◽  
S V Kirilovskiy ◽  
D A Mischenko ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Wind Tunnel ◽  
Test Section ◽  
Wind Tunnel Test ◽  
Cross Flow ◽  
Infrared Camera ◽  
Main Flow ◽  
Swept Wing ◽  
Turbulent Transition ◽  
Laminar Turbulent Transition

Abstract The laminar-turbulent transition in the boundary layer of a 45° swept wing model installed at zero attack angle in the test section of a subsonic wind-tunnel was detected with the help of an infrared camera. The camera recorded sequences of frames, the evolution of the preheated model surface temperature acquired and used for differentiating between the laminar and turbulent regions. The transition onset was evaluated at both sides of the model. Corresponding main flow computations in the virtual wind tunnel test section were performed at the same flow conditions with ANSYS Fluent. The computed main-flow velocity profiles along inviscid streamlines were used for analysis of hydrodynamic stability of the boundary layer with respect to Tollmien-Schlichting waves and stationary cross-flow vortices to obtain N-factor distributions along the model chord. A comparison of the experimental and the computed transition onsets was performed.

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