Wind-Tunnel Test of Flow Control around Half Wing Model for DBD-PA Application on UAV

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.

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

WARTA ARDHIA ◽

10.25104/wa.v42i3.242.123-138 ◽

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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Fluidic actuators for separation control at the engine/wing junction

Aircraft Engineering and Aerospace Technology ◽

10.1108/aeat-01-2017-0013 ◽

2017 ◽

Vol 89 (5) ◽

pp. 709-718 ◽

Cited By ~ 2

Author(s):

Philipp Schloesser ◽

Michael Meyer ◽

Martin Schueller ◽

Perez Weigel ◽

Matthias Bauer

Keyword(s):

Wind Tunnel ◽

Flow Control ◽

Flow Separation ◽

Mass Flux ◽

Large Scale ◽

Active Flow Control ◽

Wind Tunnel Test ◽

Local Flow ◽

Content Type ◽

Active Flow

Purpose The area behind the engine/wing junction of conventional civil aircraft configurations with underwing-mounted turbofans is susceptible to local flow separation at high angles of attack, which potentially impacts maximum lift performance of the aircraft. This paper aims to present the design, testing and optimization of two distinct systems of fluidic actuation dedicated to reduce separation at the engine/wing junction. Design/methodology/approach Active flow control applied at the unprotected leading edge inboard of the engine pylon has shown considerable potential to alleviate or even eliminate local flow separation, and consequently regain maximum lift performance. Two actuator systems, pulsed jet actuators with and without net mass flux, are tested and optimized with respect to an upcoming large-scale wind tunnel test to assess the effect of active flow control on the flow behavior. The requirements and parameters of the flow control hardware are set by numerical simulations of project partners. Findings The results of ground test show that full modulation of the jets of the non-zero mass flux actuator is achieved. In addition, it could be shown that the required parameters can be satisfied at design mass flow, and that pressure levels are within bounds. Furthermore, a new generation of zero-net mass flux actuators with improved performance is presented and described. This flow control system includes the actuator devices, their integration, as well as the drive and control electronics system that is used to drive groups of actuators. Originality/value The originality is given by the application of the two flow control systems in a scheduled large-scale wind tunnel test.

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Design and Application of an all Moving Wing Model Limiting and Locking Device

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.753-755.1031 ◽

2013 ◽

Vol 753-755 ◽

pp. 1031-1034 ◽

Cited By ~ 1

Author(s):

Bo Lu ◽

Bin Bin Lv ◽

Li Yu ◽

Hong Tao Guo ◽

Yu Yan ◽

...

Keyword(s):

Wind Tunnel ◽

Test Data ◽

High Speed ◽

Wind Tunnel Test ◽

Test Equipment ◽

Test Model ◽

Wing Flutter ◽

Wing Model ◽

Control Principle ◽

Design And Application

To effectively excite the all moving wing flutter model and limiting or quick locking model in case of bigger amplitude of the model, an excitation and limiting and locking device is designed for the high-speed wind tunnel flutter test model. This paper introduces the structure arrangement, control principle and strategy of this device. The wind tunnel flutter test indicates that this device can enhance the SNR of the test data, improve the boundary prediction precision of flutter, prevent the model from entering the flutter divergence state and protect the model and wind tunnel test equipment.

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Experimental and Numerical Studies on Static Aeroelastic Behaviours of a Forward-Swept Wing Model

Shock and Vibration ◽

10.1155/2021/5535192 ◽

2021 ◽

Vol 2021 ◽

pp. 1-12

Author(s):

Yan Ouyang ◽

Kaichun Zeng ◽

Xiping Kou ◽

Yingsong Gu ◽

Zhichun Yang

Keyword(s):

Wind Tunnel ◽

Dynamic Pressure ◽

Wind Tunnel Test ◽

Swept Wing ◽

Lattice Method ◽

Model Calculations ◽

Wind Tunnel Tests ◽

Model Based ◽

Wing Model ◽

Fidelity Model

The static aeroelastic behaviours of a flat-plate forward-swept wing model in the vicinity of static divergence are investigated by numerical simulations and wind tunnel tests. A medium fidelity model based on the vortex lattice method (VLM) and nonlinear structural analysis is proposed to calculate the displacements of the wing structure with large deformation. Follower forces effect and geometric nonlinearity are considered to calculate the deformation of the wing by finite element method (FEM). In the wind tunnel tests, the divergence dynamic pressure is predicted by the Southwell method, and the static aeroelastic displacement is measured by a photogrammetric method. The results obtained by the medium fidelity model calculations show reasonable agreement with wind tunnel test results. A high fidelity model based on coupled computational fluid dynamics (CFD) and computational structural dynamics (CSD) predicts better results of the wing tip displacement when the freestream dynamic pressure is approaching the divergence dynamic pressure.

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Wind Tunnel Experiments with Active Flow Control for an Outer Wing Model

33rd AIAA Applied Aerodynamics Conference ◽

10.2514/6.2015-2728 ◽

2015 ◽

Cited By ~ 4

Author(s):

Vlad Ciobaca ◽

Jochen Wild ◽

Matthias Bauer ◽

Thomas Grund ◽

Claus-Philipp Huehne ◽

...

Keyword(s):

Wind Tunnel ◽

Flow Control ◽

Active Flow Control ◽

Wind Tunnel Experiments ◽

Wing Model ◽

Active Flow

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Structural and Aeroelastic Studies of Wing Model with Metal Additive Manufacturing for Transonic Wind Tunnel Test by NACA 0008 Example

Aerospace ◽

10.3390/aerospace8080200 ◽

2021 ◽

Vol 8 (8) ◽

pp. 200

Author(s):

Natsuki Tsushima ◽

Kenichi Saitoh ◽

Hitoshi Arizono ◽

Kazuyuki Nakakita

Keyword(s):

Additive Manufacturing ◽

Wind Tunnel ◽

Wind Tunnel Test ◽

Wind Tunnel Testing ◽

Manufacturing Costs ◽

Aerospace Structures ◽

Manufacturing Technique ◽

Wing Model ◽

Transonic Flutter ◽

Transonic Wind Tunnel

Additive manufacturing (AM) technology has a potential to improve manufacturing costs and may help to achieve high-performance aerospace structures. One of the application candidates would be a wind tunnel wing model. A wing tunnel model requires sophisticated designs and precise fabrications for accurate experiments, which frequently increase manufacturing costs. A flutter wind tunnel testing, especially, requires a significant cost due to strict requirements in terms of structural and aeroelastic characteristics avoiding structural failures and producing a flutter within the wind tunnel test environment. The additive manufacturing technique may help to reduce the expensive testing cost and allows investigation of aeroelastic characteristics of new designs in aerospace structures as needed. In this paper, a metal wing model made with the additive manufacturing technique for a transonic flutter test is studied. Structural/aeroelastic characteristics of an additively manufactured wing model are evaluated numerically and experimentally. The transonic wind tunnel experiment demonstrated the feasibility of the metal AM-based wings in a transonic flutter wind tunnel testing showing the capability to provide reliable experimental data, which was consistent with numerical solutions.

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Structural Design, Manufacturing, and Wind Tunnel Test of a Small Expandable Wing

Key Engineering Materials ◽

10.4028/www.scientific.net/kem.306-308.1157 ◽

2006 ◽

Vol 306-308 ◽

pp. 1157-1162 ◽

Cited By ~ 4

Author(s):

Yudi Heryawan ◽

Hoon Cheol Park ◽

Nam Seo Goo ◽

Kwang Joon Yoon ◽

Yung Hwan Byun

Keyword(s):

Wind Tunnel ◽

Structural Design ◽

Wind Tunnel Test ◽

Carbon Composite ◽

Small Scale ◽

Composite Sheet ◽

Wing Model ◽

Ratio Change ◽

Lift And Drag ◽

Wing Folding

This paper describes design, manufacturing, and wind tunnel test of a motor-driven small-scale expandable wing for MAV class vehicles. The bird-like expandable wing has been developed for investigating the influence of aspect ratio change on the lift and drag of the wing. As a typical bird wing, the wing is separated into inner and outer wings. The wing model consists of the linkage system made of carbon composite strip/rod and the remaining part covered with carbon composite sheet and multiple LIPCAs (Lightweight Piezo-Composite Actuators) mimicking wing feathers. The LIPCA actuator was used to control wing camber, which created additional lift. Wind tunnel tests were conducted to investigate the changes in lift and drag during wing folding and expansion, and to observe the influence of LIPCA actuation on the wing. In the tests, effects of the wing fold/expansion and actuation of LIPCA on changes in lift and drag were quantitatively identified.

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