Wind Tunnel Test on Cable Dome of Geiger Type

2007 ◽  
Vol 2 (3) ◽  
pp. 218-224 ◽  
Author(s):  
Zhi-hong Zhang ◽  
Yukio Tamura
Keyword(s):  
Wind Tunnel ◽  
Dynamic Instability ◽  
Wind Tunnel Test ◽  
Harmonic Excitation ◽  
Degree Of Freedom ◽  
Shaking Table ◽  
Frequency Components ◽  
The One ◽  
Cable Dome ◽  
Cauchy Number

This paper presents preliminary results of an aeroelastic wind tunnel test on a cable dome. The structural design of the model is given in detail. Similarity requirements based on dimensional analysis are discussed, including Froude number, Cauchy number, and Scruton number. Structural tests are conducted on the aeroelastic model. Dynamic instability subject to harmonic excitation like a single-degree-of-freedom hardening system is verified. Both odd and even frequency components are excited when the shaking table shakes at 29Hz. For the one-degree-of-freedom Duffing model, even frequency components will be impossible due to the symmetry of the motion equation if symmetry-breaking bifurcation behaviors do not occur. Phase plane is checked and discussed when the shaking table shakes at 7Hz. A strange attractor appears to exist on the basis of the Poincare map. Some statistical results of wind tunnel tests are presented. The possibility of aeroelastic instability of the cable dome is discussed.

Wind Tunnel Test and Wind Effects on Cable Dome

2006 ◽  
Author(s):  
Zhi-hong Zhang ◽  
Yukio Tamura
Keyword(s):  
Wind Tunnel ◽  
Dynamic Instability ◽  
Wind Tunnel Test ◽  
Harmonic Excitation ◽  
Shaking Table ◽  
Aeroelastic Model ◽  
Frequency Components ◽  
The One ◽  
Cable Dome ◽  
Cauchy Number

This paper presents preliminary results of an aeroelastic wind tunnel test on a cable dome. The structural design of the model is given in detail. Similarity requirements based on dimensional analysis are discussed, including Froude number, Cauchy number and Scruton number. Structural tests are conducted on the aeroelastic model. Dynamic instability subject to harmonic excitation like SDOF hardening system is verified. Both odd and even frequency components are excited when the shaking table dowels at 29Hz. For the one-degree-of-freedom Duffing model, even frequency components will be impossible due to the symmetry of the motion equation if symmetry-breaking bifurcation behaviors do not occur. Phase plane is checked and discussed when the shaking table dowels at 7Hz. A strange attractor is found from Poincare map. Some statistical results of wind tunnel tests are presented. The possibility of aeroelasic instability of the cable dome is discussed.

Wind Tunnel Testing of Composite Wing Flutter Speed due to Control Surface Excitation

2013 ◽  
Vol 315 ◽  
pp. 359-363 ◽  
Author(s):  
Mahzan Muhammad Iyas ◽  
Muhamad Sallehuddin ◽  
Mat Ali Mohamed Sukri ◽  
Mansor Mohd Shuhaimi
Keyword(s):  
Wind Tunnel ◽  
Dynamic Instability ◽  
Wind Tunnel Test ◽  
Control Surface ◽  
Wind Tunnel Testing ◽  
Structural Stiffness ◽  
Wing Flutter ◽  
Flutter Speed ◽  
Surface Excitation ◽  
Composite Wing

Flutter is a dynamic instability problem represents the interaction among aerodynamic forces and structural stiffness during flight. The study was conducted to investigate whether deflecting the control surface will affect the flutter speed and the flutter frequency. A wind tunnel test was performed using a flat plate wing made of composite material. It was found that by deflecting the control surface at 45°, the wing entered flutter state at wind speed of 28.1 m/s instead of 33.4 m/s. In addition, the flutter frequency also reduced from 224.52 Hz to 198.96 Hz. It was concluded that by deflecting the control surface, the wing experienced flutter at lower speed and frequency.

Composite Wing Flutter Speed and Frequency due to Variable Control Surface Deflection in Low Speed Wind Tunnel

2013 ◽  
Vol 390 ◽  
pp. 3-7
Author(s):  
Muhammad Iyas Mahzan ◽  
Sallehuddin Muhamad ◽  
Sa’ardin Abdul Aziz ◽  
Mohamed Sukri Mat Ali
Keyword(s):  
Wind Tunnel ◽  
Dynamic Instability ◽  
Wind Tunnel Test ◽  
Control Surface ◽  
Wing Flutter ◽  
Flutter Speed ◽  
Surface Deflection ◽  
Relationship Of ◽  
Low Speed Wind Tunnel ◽  
The Relationship

Flutter is a dynamic instability problem represents the interaction among structural, aerodynamic, elastic and inertial forces and occurred when the energy is continuously transformed by the surrounding fluids to a flying structure in the form of kinetic energy. The study was conducted to investigate the relationship of the control surface deflection angle to the flutter speed and the flutter frequency. A wind tunnel test was performed using a flat plate wing made of composite material. It was found that by deflecting the control surface up to 45°, the flutter speed reduced almost linearly from 35.6 m/s to 22.7 m/s. The flutter frequency greatly reduced from 48 Hz without the control surface deflected to 34 Hz with the control surface deflected at 15°. After 15° deflection up to 45°, the flutter frequency reduced almost linearly.

The Test Study of Shape Coefficient of Low-Rise Buildings Roof with Different Positions of Openings

2012 ◽  
Vol 446-449 ◽  
pp. 3092-3095
Author(s):  
Ji Zhou ◽  
Yuan Ming Dou ◽  
Xi Yuan Liu ◽  
Ji Shu Sun
Keyword(s):  
Wind Tunnel ◽  
Pressure Measurement ◽  
Wind Tunnel Test ◽  
Wind Pressure ◽  
Wind Damage ◽  
Building Roof ◽  
Wind Resistance ◽  
Shape Coefficient ◽  
Test Study ◽  
The One

The majority of low-rise buildings are generally susceptible to wind damage in previous wind disaster, thus it is necessary to gain understanding of the characteristics of wind pressure for these types of building. Based on Wind Tunnel Test, the shape coefficients were studied with pressure measurement on gable roofs laying aside purlin of low-rise building roof in this paper. Three aspects were arerespectively discussed: the lows of shape coefficients and the shape coefficient value with specific wind angle on roofs of the houses completely closed, the house opened doors and windows and the house opened the hole on roof with different wind angle. The laws of shape coefficients were propounded for low-rise buildings with different positions of openings in contrast to load code. A detailed analysis of the experimental results shows that the shape coefficients will increase notably when there are the openings on metope and on roof, and the one is outward of roof, another is inward of roof. It is expected that the results should be valuable for the wind-resistance design of low-rise buildings.

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.

scholarly journals Research on High Brightness Light Source Equipment for Wind Tunnel Test

2019 ◽  
Vol 288 ◽  
pp. 02008
Author(s):  
XUE Fei ◽  
MING Chengdong ◽  
WANG Huaqiang ◽  
WANG Yuchao
Keyword(s):  
Wind Tunnel ◽  
Light Source ◽  
Wind Tunnel Test ◽  
Degree Of Freedom ◽  
Image Analysis System ◽  
Supersonic Wind Tunnel ◽  
High Brightness ◽  
Path System ◽  
Analysis System ◽  
Six Degree Of Freedom

The experimental technology of high brightness light source was studied in sub-transonic supersonic wind tunnel. The elevation light source should be installed on the smooth wall of the tunnel, and the elevation camera should be installed in the safe area of the lower wall of the wind tunnel. The falling image of the missile model in the test is reflected into the elevation camera through a reflector mounted on a curved knife. The full trajectory images and aerodynamic parameters of projectiles of embedded weapons in aircraft can be obtained by the wind tunnel dual-view angle, high brightness light path system and six-degree-of-freedom image analysis system. The newly developed high brightness light source system makes the image clearer and the accuracy of model angle of attack identification less than 0.2 degrees, which is conducive to the analysis of model trajectory. The optical system is designed reasonably, so that the motion trajectory and six-degree-of-freedom data of the model can be obtained easily by using the dual-view technology. Wind tunnel tests under complex aerodynamic conditions of sub-transonic supersonic and multi-body interference have been completed, and all parameters have reached or surpassed the existing technical indicators, meeting the requirements of wind tunnel test research on ejection of embedded weapons in aircraft.

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
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