Transonic and Low Supersonic Wind-Tunnel Tests on a Wing with Inboard Control Surface. Part I. General Description.

Supersonic wind tunnel tests of panel noise transmission

10.2514/6.1999-1962 ◽

1999 ◽

Author(s):

M. Simpson ◽

G. Mathur ◽

B. Tran ◽

C. Chin ◽

J. Lee ◽

...

Keyword(s):

Wind Tunnel ◽

Supersonic Wind Tunnel ◽

Wind Tunnel Tests ◽

Noise Transmission

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Wind tunnel tests of the inverted joined wing and a comparison with CFD results

Aircraft Engineering and Aerospace Technology ◽

10.1108/aeat-11-2016-0195 ◽

2018 ◽

Vol 90 (4) ◽

pp. 586-601

Author(s):

Cezary Galinski ◽

Grzegorz Krysztofiak ◽

Marek Miller ◽

Pawel Ruchala ◽

Marek Kalski ◽

...

Keyword(s):

Wind Tunnel ◽

Aerodynamic Characteristics ◽

Control Surface ◽

Dual Use ◽

Wind Tunnel Tests ◽

Content Type ◽

Flying Qualities ◽

Computational Fluid Dynamics Cfd ◽

Joined Wing ◽

Surface Deflections

Purpose The purpose of this paper is to present the methodology and approach adapted to conduct a wind tunnel experiment on the inverted joined-wing airplane flying model together with the results obtained. Design/methodology/approach General assumptions underlying the dual-use model design are presented in this paper. The model was supposed to be used for both wind tunnel tests and flight tests that significantly drive its size and internal structure. Wind tunnel tests results compared with the outcome of computational fluid dynamics (CFD) were used to assess airplane flying qualities before the maiden flight was performed. Findings Extensive data about the aerodynamic characteristics of the airplane were collected. Clean configurations in symmetric and asymmetric cases and also configurations with various control surface deflections were tested. Practical implications The data obtained experimentally made it possible to predict the performance and stability properties of the unconventional airplane and to draw conclusions on improvements in further designs of this configuration. Originality/value The airplane described in this paper differs from frequently analyzed joined-wing configurations, as it boasts a front lifting surface attached at the top of the fuselage, whereas the aft one is attached at the bottom. The testing technique involving the application of a dual-use model is also innovative.

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Supersonic wind-tunnel tests of wavy-walled cylinders.

AIAA Journal ◽

10.2514/3.4028 ◽

1967 ◽

Vol 5 (3) ◽

pp. 595-597 ◽

Cited By ~ 1

Author(s):

WILLIAM J. ANDERSON

Keyword(s):

Wind Tunnel ◽

Supersonic Wind Tunnel ◽

Wind Tunnel Tests

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Wind Tunnel Tests of the Tu-154M Aircraft Aerodynamic Characteristics

Journal of KONES ◽

10.2478/kones-2019-0064 ◽

2019 ◽

Vol 26 (3) ◽

pp. 113-120

Author(s):

Andrzej Krzysiak

Keyword(s):

Wind Tunnel ◽

Aerodynamic Characteristics ◽

Full Scale ◽

Control Surface ◽

Rolling Moment ◽

Wind Tunnel Tests ◽

Aircraft Model ◽

University Of Technology ◽

The Military ◽

Control Surfaces

Abstract Determination of possible manoeuvres to be performed by the aircraft requires knowledge of its aerodynamic characteristics including, in particular, characteristics of the aircraft at configuration with deflected control surfaces. In this article, the wind tunnel tests results of the model of passenger Tu-154M aircraft manufactured at the scale 1:40 are presented. The model was designed and manufactured by the Military University of Technology based on the Tu-154M aircraft geometry obtained by full-scale object scanning. The model mapped all aircraft control surfaces, along with the gaps between these surfaces and the main wing part. During the tests all the model’s control surface like, flaps, ailerons, spoilers, slots, rudder, elevator and tail plane were deflected at the same deflection angles range as they are used in the full scale aircraft. The aerodynamic characteristics of the tested Tu-154M aircraft model were measured by the 6-component internal balance. Based on the obtained measurements the aircraft model aerodynamic coefficients were calculated. In the article the basic aerodynamic characteristics of the tested Tu-154M aircraft model i.e. lift, drag coefficients as well as pitching, yawing and rolling moment coefficients versus model angles of attack and sideslip angles were presented. The tests were performed in the Institute of Aviation low speed wind tunnels T-1 of the 1.5 m diameter test section at the undisturbed velocity, V∞ = 40 m/s.

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Acquisition of Swept Aerodynamic Data by the Consecutive Changing of Wing Model Configuration in a Wind Tunnel Test Using Remote Feedback Control

Aerospace ◽

10.3390/aerospace8080217 ◽

2021 ◽

Vol 8 (8) ◽

pp. 217

Author(s):

Ken Wakimoto ◽

Kazuhisa Chiba ◽

Hiroyuki Kato ◽

Kazuyuki Nakakita

Keyword(s):

Feedback Control ◽

Wind Tunnel ◽

Deflection Angle ◽

Wind Tunnel Test ◽

Control Surface ◽

Wind Tunnel Tests ◽

The Deflection Angle ◽

Physical Phenomena ◽

3D Wing ◽

Remote Feedback

This study conducted wind tunnel tests with consecutive deflection angle changes on a three-dimensional (3D) wing with a control surface to procure aerodynamic data by sweeping the deflection angle. Configuration changes of a wind tunnel test model, such as changing the deflection angle of control surfaces, are usually performed manually with the ventilation suspended. Hence, the number of configurations that can be implemented within a confined test period is restricted; the aerodynamic data gained are discrete values. To accomplish continuous angular modulation would dramatically improve the ability by sweeping through the aerodynamic data in wind tunnel tests, enhancing the test system as a tool for discussing complex physical phenomena. Thus, this study created a compact remote feedback control system using optical measurement to continuously obtain high-precision aerodynamic data without stopping the wind tunnel, eliminating human operation. In particular, this study targets a 3D wing wind tunnel model with a control surface, which is more challenging to fabricate, miniaturizing the system in a model. The system consequently attained consecutive aerodynamic data multiple times under numerous configurations, which had been impracticable to reach in the past, within a wind tunnel test period of several days, thereby dramatically increasing the testing capability. The reproducibility was quantitatively verified by comparing the multiple data for the identical configurations. Furthermore, the reliability was demonstrated using discrete data obtained by conventional stepwise deflection angle adjustments. Eventually, the system was able to grasp physical phenomena involving hysteresis.

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HB-2 high-velocity correlation model at high angles of attack in supersonic wind tunnel tests

Chinese Journal of Aeronautics ◽

10.1016/j.cja.2019.03.022 ◽

2019 ◽

Vol 32 (7) ◽

pp. 1565-1576 ◽

Cited By ~ 1

Author(s):

Djordje VUKOVIĆ ◽

Dijana DAMLJANOVIĆ

Keyword(s):

Wind Tunnel ◽

High Velocity ◽

Correlation Model ◽

Velocity Correlation ◽

Supersonic Wind Tunnel ◽

Wind Tunnel Tests ◽

High Angles Of Attack

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Test rig dedicated for hardware used in wind tunnels

Technical Sciences ◽

10.31648/ts.7128 ◽

2021 ◽

Author(s):

Aleksandra Ordon ◽

Paulina Kurnyta-Mazurek

Keyword(s):

Wind Tunnel ◽

Measurement System ◽

Experimental Studies ◽

Control Surface ◽

Test Rig ◽

Paper Test ◽

Wind Tunnel Tests ◽

Rotor Position ◽

Labview Software ◽

Time Histories

The paper present the results of work on measurement system dedicated to hardware used during wind tunnel tests, especially to servomechanisms. These devices could be applied to set specific position of control surface. Proposed system would ensure continuous monitoring of servo-rotor position and servo-motor temperature and would avoid uncontrolled change of control surface position. The application designed to monitor the operating status of the servomechanism was prepared in the LabVIEW software and was implemented on the myRIO platform. Developed test rig allow to register time histories of servo-rotor position and temperature during for different values of applied load. In the paper, test methodology were also presented. Experimental studies show that before wind tunnel tests, selected servomechanism should be tested in terms of maintaining the parameters declared by the manufacturer, especially during continuous operation. Developed measurement system can be used during wind tunnel tests, as well as only for servo-mechanism parameter testing.

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