scholarly journals Wind Tunnel Measurement Systems for Unsteady Aerodynamic Forces on Bluff Bodies: Review and New Perspective

Sensors ◽  
2020 ◽  
Vol 20 (16) ◽  
pp. 4633
Author(s):  
Zengshun Chen ◽  
Yemeng Xu ◽  
Hailin Huang ◽  
Kam Tim Tse
Keyword(s):  
Wind Tunnel ◽  
Forced Vibration ◽  
Wind Tunnel Test ◽  
Force Balance ◽  
Vibration Test ◽  
Bluff Bodies ◽  
Test Model ◽  
Test Technique ◽  
Forced Vibration Test ◽  
New Perspective

Wind tunnel tests have become one of the most effective ways to evaluate aerodynamics and aeroelasticity in bluff bodies. This paper has firstly overviewed the development of conventional wind tunnel test techniques, including high frequency base balance technique, static synchronous multi-pressure sensing system test technique and aeroelastic test, and summarized their advantages and shortcomings. Subsequently, two advanced test approaches, a forced vibration test technique and hybrid aeroelastic- force balance wind tunnel test technique have been comprehensively reviewed. Then the characteristics and calculation procedure of the conventional and advanced wind tunnel test techniques were discussed and summarized. The results indicated that the conventional wind tunnel test techniques ignored the effect of structural oscillation on the measured aerodynamics as the test model is rigid. A forced vibration test can include that effect. Unfortunately, a test model in a forced vibration test cannot respond like a structure in the real world; it only includes the effect of structural oscillation on the surrounding flow and cannot consider the feedback from the surrounding flow to the oscillation test model. A hybrid aeroelastic-pressure/force balance test technique that can observe unsteady aerodynamics of a test model during its aeroelastic oscillation completely takes the effect of structural oscillation into consideration and is, therefore, effective in evaluation of aerodynamics and aeroelasticity in bluff bodies. This paper has not only advanced our understanding for aerodynamics and aeroelasticity in bluff bodies, but also provided a new perspective for advanced wind tunnel test techniques that can be used for fundamental studies and engineering applications.

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

Investigation of winglet on the transonic flutter characteristics for a wind tunnel test model CHNT-1

2019 ◽  
Vol 86 ◽  
pp. 430-437 ◽  
Author(s):  
Binbin Lv ◽  
Zhiliang Lu ◽  
Tongqing Guo ◽  
Di Tang ◽  
Li Yu ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Test Model ◽  
Transonic Flutter

Videogrammetric Techniques for Wind Tunnel Testing and Applications

2014 ◽  
Vol 986-987 ◽  
pp. 1629-1633
Author(s):  
Zheng Yu Zhang ◽  
Xu Hui Huang ◽  
Jiang Yin ◽  
Han Xuan Lai
Keyword(s):  
Wind Tunnel ◽  
Wave Front ◽  
High Speed ◽  
Marked Point ◽  
Wind Tunnel Test ◽  
Wind Tunnels ◽  
Test Model ◽  
Wind Tunnel Testing ◽  
Section Size ◽  
Key Techniques

Videogrammetric measurement is a research focus for the organizations of wind tunnel test because of its no special requirements on the test model, its key techniques for the vibration environment of the high speed wind tunnel are introduced by this paper, such as the solution of exterior parameters with big-angle large overlap, the algorithm of image processing for extracting marked point, the method of camera calibration and wave-front distortion field measurement. The great requirements and application prospects of videogrammetry in wind tunnel fine testing have been demonstrated by several practice experiments, including to measure test model’s angle of attack, dynamic deformations and wave-front distortion field in high speed wind tunnels whose test section size is 2 meters.

Static aero-elastic analysis of wind tunnel test model in transonic flow

2020 ◽  
Author(s):  
P. K. Siddalingappa ◽  
A. P. Dharmendra ◽  
Santosh Hosur ◽  
Prashant Manvi
Keyword(s):  
Wind Tunnel ◽  
Transonic Flow ◽  
Wind Tunnel Test ◽  
Test Model ◽  
Elastic Analysis

scholarly journals Remote and Feedback Control of the Flap Angle in a Wind Tunnel Test Model by Optical Measurement

Aerospace ◽  
2020 ◽  
Vol 7 (2) ◽  
pp. 11
Author(s):  
Kazuhisa Chiba ◽  
Tatsuro Komatsu ◽  
Hiroyuki Kato ◽  
Kazuyuki Nakakita
Keyword(s):  
Feedback Control ◽  
Wind Tunnel ◽  
Optical Measurement ◽  
Wind Tunnel Test ◽  
Measurement Technology ◽  
Test Model ◽  
Measurement Equipment ◽  
Feedback Control System ◽  
Aerodynamic Coefficients ◽  
Japan Aerospace Exploration Agency

We have developed a remote and precise feedback control system using optical measurement technology to alter the angle of a flap, which is part of a wind tunnel test model, automatically and to earn the aerodynamic data efficiently. To rectify the wasteful circumstance that Japan Aerospace Exploration Agency (JAXA)’s low-turbulence wind tunnel stops ventilation every time to switch model configurations, we repaired hardware for remote operation and generated software for feedback control. As a result, we have accomplished a system that dramatically advances the efficiency of wind tunnel tests. Moreover, the system was able to consider the deformation of the model through optical measurement; the system controlled flap angles with errors less than the minimum resolution of optical measurement equipment. Consequently, we successfully grasped the nonlinearity of three aerodynamic coefficients C L , C D , and C M p that was impossible so far.

scholarly journals Desain dan Eksperimen Uji Getaran di Tanah dari Model Separuh Sayap Pesawat N219

WARTA ARDHIA ◽  
2017 ◽  
Vol 42 (3) ◽  
pp. 123
Author(s):  
Sayuti Syamsuar ◽  
Leonardo Gunawan ◽  
Martina Widiramdhani ◽  
Nina Kartika
Keyword(s):  
Wind Tunnel ◽  
Critical Phenomenon ◽  
Damping Ratio ◽  
Wind Tunnel Test ◽  
Ground Vibration ◽  
Parameter Analysis ◽  
Vibration Test ◽  
Software Analysis ◽  
Flutter Speed ◽  
Wing Model

Fenomena flutter merupakan salah satu fenomena yang kritis dan dapat membahayakan pesawat. Ketika, pesawat terbang semakin cepat dan mencapai kecepatan flutter, maka akan terjadi ketidakstabilan struktur. Oleh sebab itu, untuk menjamin keselamatan Pilot saat uji terbang, perlu dilakukan analisis awal pada kecepatan flutter. Uji terowongan angin selalu dilakukan untuk memvalidasi hasil dari analisis numerikal. Penelitian ini meliputi analisis program NASTRAN pada model separuh sayap pesawat N219 saat uji getaran di tanah. Prediksi kecepatan flutter secara analisis hampir sama dengan hasil uji terowongan angin. Parameter modus struktur yang ditemukan, seperti frekuensi natural, modus getar dan rasio redaman, dapat digunakan untuk analisis parameter flutter sebagai metoda analisis baru. [The Design and Experiment of Ground Vibration Test of N219 Aircraft Half Wing Model] Flutter phenomena is a critical phenomenon that can be dangerous for aircraft. When an aircraft fly faster until reach flutter speed, the structure will become unstable. Therefore, it is important to conduct preliminary analysis of flutter speed to ensure the safety of Pilot. Wind tunnel test is necessary to be conducted to validate numerical analysis results. This research consist of NASTRAN software analysis of half wing model of N219 aircraft for ground vibration test. The prediction of flutter speed which is obtained from software analysis is similar with the wind tunnel test result. It is found that the modus parameter of structure like natural frequency, modus of vibration and damping ratio can be used on the parameter analysis as a new analysis method.

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