Effects of Aircraft Tail Configurations on Sensitivity to Yaw Disturbances

2014 ◽  
Vol 629 ◽  
pp. 197-201 ◽  
Author(s):  
Nur Amalina Musa ◽  
S. Mansor ◽  
Airi Ali ◽  
Wan Zaidi Wan Omar ◽  
Ainullotfi Abdul Latif ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Aerodynamic Characteristics ◽  
Low Speed ◽  
Stability And Control ◽  
Directional Stability ◽  
And Control ◽  
Low Speed Wind Tunnel ◽  
Yaw Moment ◽  
Made In

A wind tunnel test was conducted to compare the characteristics of low speed stability and control for aircraft with conventional tail and V-tail configurations. Comparison was made in terms of static directional stability at selected test speed of 40 m/s, which corresponds to Reynolds number of 0.1622 x 106 based on the chord. Three types of simplified tail-only model were tested in Universiti Teknologi Malaysia's Low Speed Wind Tunnel (UTM-LST). Results show that the V-tail configuration greatly affects the aerodynamic characteristics in directional stability as the side force and yaw moment tends to vary linearly with yaw angles up to 25 degrees, compared to conventional tail that has linear characteristics up to only 10 degrees yaw

Study on the Aerodynamic Characteristics and Galloping Instability of Conductors Covered with Sector-Shaped Ice by a Wind Tunnel Test

2020 ◽  
Vol 20 (06) ◽  
pp. 2040016
Author(s):  
Jia-Xiang Li ◽  
Jian Sun ◽  
Ye Ma ◽  
Shu-Hong Wang ◽  
Xing Fu
Keyword(s):  
Wind Tunnel ◽  
Drag Coefficient ◽  
Wind Tunnel Test ◽  
Aerodynamic Characteristics ◽  
Ice Thickness ◽  
Shape Parameters ◽  
Aerodynamic Coefficient ◽  
Wind Tunnel Tests ◽  
And Control

Conductors with sector-shaped ice are susceptible to galloping. To prevent and control galloping, it is necessary to study the conductor aerodynamic characteristics. Wind tunnel tests were performed to study the influence of two shape parameters (ice thickness and ice angle) of a conductor with sector-shaped ice on the aerodynamic characteristics considering the roughness of the surface. In addition, the unstable areas for galloping are discussed according to Den Hartog theory and Nigol theory. The results show that with increasing ice thickness, the aerodynamic coefficient curves fluctuate more strongly, and galloping tends to occur; with increasing ice angle, the unstable area becomes larger according to Nigol theory, and the increasing drag coefficient will suppress the unstable areas according to Den Hartog theory. With the increasing two shape parameters, the most affected ranges of the aerodynamic coefficient curves are 150–180∘.

LOW SPEED WIND TUNNEL TEST OF THE JET TRAINER MODEL AT HIGH ANGLES OF ATTACK

2016 ◽  
Vol 23 (4) ◽  
pp. 471-478
Author(s):  
Kamil Smędra ◽  
Rafał Świerkot ◽  
Krzysztof Kubryński
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Low Speed ◽  
Low Speed Wind Tunnel ◽  
High Angles Of Attack

Development and validation of an enhanced semi-empirical method for estimation of aerodynamic characteristics of light, propeller-driven airplanes

2016 ◽  
Vol 232 (4) ◽  
pp. 638-648 ◽  
Author(s):  
M Rostami ◽  
SA Bagherzadeh
Keyword(s):  
Wind Tunnel Test ◽  
Aerodynamic Characteristics ◽  
Empirical Method ◽  
General Aviation ◽  
Design Data ◽  
Stability And Control ◽  
Control Derivatives ◽  
Development And Validation ◽  
Semi Empirical ◽  
And Control

This study is intended to introduce an enhanced semi-empirical method for estimation of longitudinal and lateral-directional stability and control derivatives in the preliminary design phase of light airplanes. Specialised for light, single or twin propeller-driven airplanes, available state-of-the-art analytical procedures and design data compendia are combined and modified in a unique compatible method, and automated in NAMAYEH software. In the present study, modified procedures and the software structure are presented. Afterwards, the proposed method is applied to a four-place, low wing, single-engine, propeller-driven general aviation airplane. In order to validate the proposed method, the estimated aerodynamic characteristics are compared with the wind tunnel test data as well as DATCOM and VLM-based method estimations. The results indicate that the proposed method is able to predict the aerodynamic characteristics in an acceptable range of accuracy from zero-lift to stall conditions in all configurations.

A Differential Configuration of Split Drag-Rudders with Variable Bias for Directional Control of Flying-Wing

2014 ◽  
Vol 643 ◽  
pp. 54-59 ◽  
Author(s):  
Jahanzeb Rajput ◽  
Wei Guo Zhang ◽  
Xiao Bo Qu
Keyword(s):  
Cfd Simulation ◽  
Angle Of Attack ◽  
Large Angle ◽  
Simple Method ◽  
Low Speed ◽  
Control Efficiency ◽  
Stability And Control ◽  
Directional Stability ◽  
Variable Bias ◽  
And Control

The directional stability and control is crucial for the low-speed flight of a flying-wing aircraft. The split drag-rudders are well known devices used to provide directional stability and control in a flying-wing aircraft. As opposed to conventional rudders, the control efficiency of split drag-rudders is typically low for small deflection-angles and the influence on yawing moment is nonlinear. Such characteristics limit the control capability of split drag-rudders at low speed flight with large angle-of-attack. In this paper, a simple method is presented to improve the control efficiency of split drag-rudders at low speed flight with large angle-of-attack. The method is based on a strictly differential configuration of split drag-rudders which operates around a certain variable bias. The bias can be varied according to different flight conditions in order to achieve desired performance. The CFD simulation results are presented in support of this concept. Results also show that the proposed configuration has linearizing effects on yawing moment vs. deflection curves, which may prove helpful in control system design process. The possible control reversal in yaw at large angle of attack can also be avoided with this method.

Investigations on stability and control characteristics of a CS-VLA certified aircraft using wind tunnel test data

2016 ◽  
Vol 230 (14) ◽  
pp. 2728-2743 ◽  
Author(s):  
Nhu Van Nguyen ◽  
Maxim Tyan ◽  
Jae-Woo Lee ◽  
Sangho Kim
Keyword(s):  
Wind Tunnel ◽  
Test Data ◽  
Wind Tunnel Test ◽  
Stability Control ◽  
Scale Model ◽  
Control Analysis ◽  
Design Review ◽  
Stability And Control ◽  
The Stability ◽  
And Control

The stability and control characteristics using a wind tunnel test data process are proposed and developed to investigate the stability and control characteristics of a CS-VLA certified aircraft and to comply with the CS-VLA subpart B at the preliminary design review (PDR) and critical design review (CDR) stage. The aerodynamic characteristics of a 20% scale model are provided and investigated with clean, rudder, aileron, elevator, and winglet effects. The Mach and Reynolds correction methods are proposed to correct the aerodynamics of the scale model for stability and control analysis to obtain more reliable and accurate results of the full-scale model. The aerodynamic inputs and moment of inertia (MOI) comparison between the PDR and CDR stage show good agreement in the trends of stability and control derivatives. The CDR analysis results with the corrected wind tunnel test data and accurate MOI are investigated with respect to the longitudinal and lateral stability, control, and handling qualities to comply with the CS-VLA 173, CS-VLA 177, and CS-VLA 181 for finalizing the configuration in the CDR stage.

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