scholarly journals Acoustic Data Processing and Transient Signal Analysis for the Hybrid Wing Body 14- by 22-Foot Subsonic Wind Tunnel Test

2014 ◽  
Author(s):  
Christopher J. Bahr ◽  
Thomas F. Brooks ◽  
William M. Humphreys ◽  
Taylor B. Spalt ◽  
Daniel J. Stead
Keyword(s):  
Wind Tunnel ◽  
Data Processing ◽  
Signal Analysis ◽  
Wind Tunnel Test ◽  
Transient Signal ◽  
Acoustic Data ◽  
Subsonic Wind Tunnel

Aerodynamic Interference Correction Methods Case: Subsonic Closed Wind Tunnels

2012 ◽  
Vol 225 ◽  
pp. 60-66 ◽  
Author(s):  
Surjatin Wiriadidjaja ◽  
Azmin Shakrine Mohd Rafie ◽  
Fairuz Izzuddin Romli ◽  
Omar Kassim Ariff
Keyword(s):  
Wind Tunnel ◽  
Classical Method ◽  
Wind Tunnel Test ◽  
Analytical Techniques ◽  
Wind Tunnels ◽  
New Techniques ◽  
Subsonic Wind Tunnel ◽  
Small Model ◽  
Active Research ◽  
Solid Walls

The approach to problems of wall interference in wind tunnel testing is generally based on the so-called classical method, which covers the wall interference experienced by a simple small model or the neo-classical method that contains some improvements as such that it can be applied to larger models. Both methods are analytical techniques offering solutions of the subsonic potential equation of the wall interference flow field. Since an accurate description of wind tunnel test data is only possible if the wall interference phenomena are fully understood, uncounted subsequent efforts have been spent by many researchers to improve the limitation of the classical methods by applying new techniques and advanced methods. However, the problem of wall interference has remained a lasting concern to aerodynamicists and it continues to be a field of active research until the present. The main objective of this paper is to present an improved classical method of the wall interference assessment in rectangular subsonic wind tunnel with solid-walls.

Wind Tunnel Test of a Blended Wing Aircraft in Ground Effect With Active Flow Control

2016 ◽  
Author(s):  
Michael Mayo ◽  
Jonathan Carroll ◽  
Nicholas Motahari ◽  
Warren Lee ◽  
Robert Englar
Keyword(s):  
Wind Tunnel ◽  
Active Flow Control ◽  
Wind Tunnel Test ◽  
Ground Effect ◽  
Circulation Control ◽  
Wing Model ◽  
Subsonic Wind Tunnel ◽  
Test Methodology ◽  
Tunnel Floor ◽  
Lift And Drag

This paper describes the test methodology and results for a wind tunnel experiment featuring a blended wing aircraft in ground effect with built-in circulation control. A 82.55cm wingspan blended wing model was tested in a subsonic wind tunnel at velocities ranging from 18m/s – 49m/s and corresponding Reynolds numbers ranging from 130k – 350k. Pitch angle was held constant at 0 degrees and the height above the wind tunnel floor was modified to determine lift and drag modification due to ground effect. At a normalized height (y/bw) of 0.06, ground effect increased lift production by 24% and reduced drag by 22% when compared to a normalized height of 0.5. The addition of the circulation control significantly increased the lift production of the model at a cost of increased drag. At a normalized height of 0.031, the lift production increased by 200% at a blowing coefficient of 0.01, but the drag also increased by 72%, ultimately increasing L/D by 178%. Experimental results also suggest that ground effect and circulation control have a synergistic effect when used simultaneously. The effects of Reynolds number and circulation control slot height are also investigated.

scholarly journals Wind tunnel testing of powered lift, all-wing STOL model

2009 ◽  
Vol 113 (1140) ◽  
pp. 129-137 ◽  
Author(s):  
S. W. Collins ◽  
B. W. Westra ◽  
J. C. Lin ◽  
G. S. Jones ◽  
C. H. Zeune
Keyword(s):  
Wind Tunnel ◽  
State Of The Art ◽  
Wind Tunnel Test ◽  
Field Measurements ◽  
Wind Tunnel Testing ◽  
High Lift ◽  
Computational Tools ◽  
Subsonic Wind Tunnel ◽  
Model Configuration ◽  
Langley Research Center

Abstract Short take-off and landing (STOL) systems can offer significant capabilities to warfighters and, for civil operators thriving on maximising efficiencies they can improve airspace use while containing noise within airport environments. In order to provide data for next generation systems, a wind tunnel test of an all-wing cruise efficient, short take-off and landing (CE STOL) configuration was conducted in the National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC) 14ft by 22ft Subsonic Wind Tunnel. The test’s purpose was to mature the aerodynamic aspects of an integrated powered lift system within an advanced mobility configuration capable of CE STOL. The full-span model made use of steady flap blowing and a lifting centerbody to achieve high lift coefficients. The test occurred during April through June of 2007 and included objectives for advancing the state-of-the-art of powered lift testing through gathering force and moment data, on-body pressure data, and off-body flow field measurements during automatically controlled blowing conditions. Data were obtained for variations in model configuration, angles of attack and sideslip, blowing coefficient, and height above ground. The database produced by this effort is being used to advance design techniques and computational tools for developing systems with integrated powered lift technologies.

scholarly journals UNCERTAINTY IN STATIC PRESSURE CORRECTION IN A SUBSONIC WIND TUNNEL

2004 ◽  
Vol 3 (2) ◽  
Author(s):  
M. L. C. C. Reis ◽  
O. A. F. Mello ◽  
M. Chisaki
Keyword(s):  
Wind Tunnel ◽  
Static Pressure ◽  
Uncertainty Propagation ◽  
Wind Tunnel Test ◽  
Absolute Pressure ◽  
Input Quantity ◽  
Flow Parameters ◽  
Subsonic Wind Tunnel ◽  
Measured Flow ◽  
The One

The static pressure p on the subsonic Wind Tunnel of the Aerodynamic Testing Laboratory of the Institute of Aeronautics and Space – IAE, Aerospace Technical Center – CTA, is measured using an absolute pressure sensor, located on the upper test section wall. This measurement is not taken at the same location as the one where the model is mounted during the actual wind tunnel test. This fact raises the need for a correction during data reduction. The identification and evaluation of the associated error source is important because the static pressure is an input quantity for the calculation of the total pressure pt, Mach number M and density ρ during the test. The present paper is concerned with the determination of the relationship between the static pressure measured on the tunnel’s upper wall and that at the model location, and with the analysis of the uncertainty propagation for the measured flow parameters.

Wind Pressure Distribution on a Large-Span Roof Structure

2012 ◽  
Vol 166-169 ◽  
pp. 234-238
Author(s):  
Qin Hua Wang ◽  
Bi Qing Shi ◽  
Le Le Zhang
Keyword(s):  
Wind Tunnel ◽  
Data Processing ◽  
Pressure Distribution ◽  
Pressure Measurement ◽  
Wind Tunnel Test ◽  
Wind Pressure ◽  
Large Span ◽  
Roof Structure

In this paper, wind tunnel test of a large-span roof structure is firstly introduced. Secondly, data processing on synchronous multi-spots pressure measurement test is given. Wind pressure distribution is calculated by using the method mentioned in this paper. Some results and conclusion are useful for design of large-span roof structure.

scholarly journals UNCERTAINTY IN STATIC PRESSURE CORRECTION IN A SUBSONIC WIND TUNNEL

2004 ◽  
Vol 3 (2) ◽  
pp. 122
Author(s):  
M. L. C. C. Reis ◽  
O. A. F. Mello ◽  
M. Chisaki
Keyword(s):  
Wind Tunnel ◽  
Static Pressure ◽  
Wind Tunnel Test ◽  
Absolute Pressure ◽  
Input Quantity ◽  
Flow Parameters ◽  
Subsonic Wind Tunnel ◽  
Measured Flow ◽  
The One

The static pressure p on the subsonic Wind Tunnel of the Aerodynamic Testing Laboratory of the Institute of Aeronautics and Space – IAE, Aerospace Technical Center – CTA, is measured using an absolute pressure sensor, located on the upper test section wall. This measurement is not taken at the same location as the one where the model is mounted during the actual wind tunnel test. This fact raises the need for a correction during data reduction. The identification and evaluation of the associated error source is important because the static pressure is an input quantity for the calculation of the total pressure pt, Mach number M and density ρ during the test. The present paper is concerned with the determination of the relationship between the static pressure measured on the tunnel’s upper wall and that at the model location, and with the analysis of the uncertainty propagation for the measured flow parameters.

Response and Operational Modal Analysis from Wind Tunnel Test of the EOLO Flexible Aircraft

2021 ◽  
Author(s):  
David F. Castillo Zuñiga ◽  
Alain Giacobini Souza ◽  
Roberto G. da Silva ◽  
Luiz Carlos Sandoval Góes
Keyword(s):  
Wind Tunnel ◽  
Modal Analysis ◽  
Wind Tunnel Test ◽  
Operational Modal Analysis ◽  
Flexible Aircraft

DEVELOPMENT OF A RAPID PROTOTYPING METHODOLOGY FOR WIND TUNNEL TEST MODEL DESIGN

2019 ◽  
Author(s):  
Bruno Ricardo Massucatto Padilha ◽  
Guilherme Barufaldi ◽  
ROBERTO GIL ANNES DA SILVA
Keyword(s):  
Wind Tunnel ◽  
Rapid Prototyping ◽  
Wind Tunnel Test ◽  
Test Model ◽  
Model Design

Rancang Bangun Piranti Lunak Pengolah Data Pasca Pengujian Terowongan Angin Kecepatan Rendah Indonesia

2016 ◽  
Vol 7 (2) ◽  
pp. 131-138
Author(s):  
Ivransa Zuhdi Pane
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Test Results ◽  
Effective Solution ◽  
Post Processing ◽  
Prototype Development ◽  
Design Activities ◽  
Index Terms ◽  
Test Objects ◽  
Processing Requirement

Data post-processing plays important roles in a wind tunnel test, especially in supporting the validation of the test results and further data analysis related to the design activities of the test objects. One effective solution to carry out the data post-processing in an automated productive manner, and thus eliminate the cumbersome conventional manual way, is building a software which is able to execute calculations and have abilities in presenting and analyzing the data in accordance with the post-processing requirement. Through several prototype development cycles, this work attempts to engineer and realize such software to enhance the overall wind tunnel test activities. Index Terms—software engineering, wind tunnel test, data post-processing, prototype, pseudocode

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