The Effects of Split Drag Flaps on Directional Motion of UiTM’s BWB UAV Baseline-II E-4: Investigation Based on CFD Approach

Mohamad, Firdaus; Wisnoe, Wirachman; Kuntjoro, Wahyu; Nasir, Rizal Effendy Mohd

doi:10.4028/www.scientific.net/amr.433-440.584

Cited by 3 publications

(2 citation statements)

References 8 publications

(8 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The number of cells reaches about 1 million cells. Number of cell is selected based on the grid independence study that can be refered in [5]. This model was imported into CFD software to run the simulations.…”

Section: Cfd Simulationmentioning

confidence: 99%

Yaw Stability Analysis for UiTM's BWB Baseline-II UAV E-4

Mohamad

Wisnoe

Nasir

et al. 2013

AMM

Self Cite

View full text Add to dashboard Cite

This paper presents a study about yaw stability analysis for UiTMs Blended-Wing-Body (BWB) Baseline-II E-4. This aircraft is equipped with split drag flaps in order to perform directional motion. One of the split drag flaps will be deflected to generate yawing moment. This yawing moment is generated through the drag that is produced upon deflection of flaps. The study was carried out using Computational Fluid Dynamics (CFD) for various sideslip angles (β) and various flaps deflection angle (δT). The simulation was conducted at 0.1 Mach number (35 m/s) and results in terms of coefficient such yawing and rolling moment are tabulated in order to determine the stability of the aircraft. The result reveals that the aircraft is directionally unstable. This is as expected because the aircraft does not have any vertical tail configuration to provide the yawing moment. However, high deflection of split flaps can still generate adequate restoring moment for the aircraft.

show abstract

Section: Cfd Simulationmentioning

confidence: 99%

Yaw Stability Analysis for UiTM's BWB Baseline-II UAV E-4

Mohamad

Wisnoe

Nasir

et al. 2013

AMM

Self Cite

View full text Add to dashboard Cite

show abstract

“…Many verifications have been conducted to reveal above control features [5][6][7][8] in flight by numerical computation and theoretical analysis. To obtain a yaw motion of the airplane by the deflection of rudder on one side of the wing, a split drag flap was designed based on UiTM's BWB UAV Baseline-II E-4 by Firdaus Mohamad et al [9], reporting that asymmetric drag force of the wing was generated, and yawing moment was produced. The effects of different airspeeds and angles of attack on directional control were investigated in wind tunnel by Gloria Stenfelt et al [10], noting that a yaw moment was achieved through the split flap deflection on one wing.…”

Section: Introductionmentioning

confidence: 99%

Structural design and experimental verification of a novel split aileron wing

Zhao

Wen

2020

Aerospace Science and Technology

View full text Add to dashboard Cite

To improve aerodynamic performance and attain a lighter weight of wing for use in small (<30 kg) drones, a novel design scheme of split aileron is proposed based on a similar application of the split flap, which enables the airplane to operate rolling movement. The function of the separated aileron is implemented utilizing an electro-servo system that is actuated through a brushless direct current motor (BLDCM). The design of three conceptual configurations of the clam-shell aileron structure, including the upper, middle, and bottom positions with deflection angle of 31 0 and 15 0 downwards, are studied numerically and theoretically. Based on the optimal design of the bottom position of the split aileron structure, the aerodynamic characteristics and structural weight of the separated aileron are evaluated by comparison with a traditional hinged aileron. The results indicate that the proposed design of the detached aileron can enhance the average aerodynamic efficiency of the wing by 16.3 % and reduce the weight of the wing by 49.5%. The functional prototype of the split aileron wing airplane is established and manufactured based on the proposed design. The flight test results confirm applicability of the clam-shell aileron to control the rolling motion of aircraft.The split aileron is potentially exploited for the fixed-wing unmanned aerial vehicles (UAVs) in practical engineering application.

show abstract

Structural Design and Aerodynamic Characteristic of an Innovative Split Aileron Configuration

Zhao

Wen

2019

2019 IEEE 10th International Conference on Mechanical and Aerospace Engineering (ICMAE)

View full text Add to dashboard Cite

The Effects of Split Drag Flaps on Directional Motion of UiTM’s BWB UAV Baseline-II E-4: Investigation Based on CFD Approach

Cited by 3 publications

References 8 publications

Yaw Stability Analysis for UiTM's BWB Baseline-II UAV E-4

Yaw Stability Analysis for UiTM's BWB Baseline-II UAV E-4

Structural design and experimental verification of a novel split aileron wing

Structural Design and Aerodynamic Characteristic of an Innovative Split Aileron Configuration

Contact Info

Product

Resources

About