Wind Tunnel Experiments and CFD Analysis of Blended Wing Body (BWB) Unmanned Aerial Vehicle (UAV) at Mach 0.1 and Mach 0.3

In this paper, a study of aerodynamic characteristics of UiTM's Blended-Wing-Body Unmanned Aerial Vehicle (BWB-UAV) Baseline-II in terms of side force, drag force and yawing moment coefficients are presented through Computational Fluid Dynamics (CFD) simulation. A vertical rudder is added to the aircraft at the rear centre part of the fuselage as yawing control surface. The study consists of varying the side slip angles for various rudder deflection angles and to plot the results for each aerodynamic parameter. The comparison with other yawing control surface for the same aircraft obtained previously are also presented. For validation purpose, the lift and drag coefficients are compared with the results obtained from wind tunnel experiments.

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Aerodynamic Analysis of Blended Wing Body - Unmanned Aerial Vehicle (BWB-UAV) Equipped with Horizontal Stabilizers

MATEC Web of Conferences ◽

10.1051/matecconf/201925602004 ◽

2019 ◽

Vol 256 ◽

pp. 02004

Author(s):

Nornashiha Mohd Saad ◽

Wirachman Wisnoe ◽

Rizal Effendy Mohd Nasir ◽

Zurriati Mohd Ali ◽

Ehan Sabah Shukri Askari

Keyword(s):

Unmanned Aerial Vehicle ◽

Cfd Simulation ◽

Lift Coefficient ◽

Angle Of Attack ◽

Flight Test ◽

Longitudinal Direction ◽

Static Stability ◽

Pitching Moment ◽

Aerial Vehicle ◽

Blended Wing Body

This paper presents an aerodynamic characteristic study in longitudinal direction of UiTM Blended Wing Body-Unmanned Aerial Vehicle Prototype (BWB-UAV Prototype) equipped with horizontal stabilizers. Flight tests have been conducted and as the result, BWB experienced overturning condition at certain angle of attack. Horizontal stabilizer was added at different location and size to overcome the issue during the flight test. Therefore, Computational Fluid Dynamics (CFD) analysis is performed at different configuration of horizontal stabilizer using Spalart - Allmaras as a turbulence model. CFD simulation of the aircraft is conducted at Mach number 0.06 or v = 20 m/s at various angle of attack, α. The data of lift coefficient (CL), drag coefficient (CD), and pitching moment coefficient (CM) is obtained from the simulations. The data is represented in curves against angle of attack to measure the performance of BWB prototype with horizontal stabilizer. From the simulation, configuration with far distance and large horizontal stabilizer gives steeper negative pitching moment slope indicating better static stability of the aircraft.

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Rapid, International Design and Test of a Hybrid-Powered, Blended-Wing Body Unmanned Aerial Vehicle

11th AIAA Aviation Technology, Integration, and Operations (ATIO) Conference ◽

10.2514/6.2011-6964 ◽

2011 ◽

Cited By ~ 1

Author(s):

Jean Koster ◽

Claus-dieter Munz ◽

Ewald Kraemer ◽

Kee-Choon Wong ◽

Dries Verstraete ◽

...

Keyword(s):

Unmanned Aerial Vehicle ◽

Aerial Vehicle ◽

Blended Wing Body

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Design and Validation of a New Morphing Camber System by Testing in the Price—Païdoussis Subsonic Wind Tunnel

Aerospace ◽

10.3390/aerospace7030023 ◽

2020 ◽

Vol 7 (3) ◽

pp. 23 ◽

Cited By ~ 1

Author(s):

David Communier ◽

Ruxandra Mihaela Botez ◽

Tony Wong

Keyword(s):

Wind Tunnel ◽

Unmanned Aerial Vehicle ◽

Lift Coefficient ◽

Angle Of Attack ◽

Leading Edge ◽

Trailing Edge ◽

Subsonic Wind Tunnel ◽

Aerial Vehicle ◽

Stall Angle

This paper presents the design and wind tunnel testing of a morphing camber system and an estimation of performances on an unmanned aerial vehicle. The morphing camber system is a combination of two subsystems: the morphing trailing edge and the morphing leading edge. Results of the present study show that the aerodynamics effects of the two subsystems are combined, without interfering with each other on the wing. The morphing camber system acts only on the lift coefficient at a 0° angle of attack when morphing the trailing edge, and only on the stall angle when morphing the leading edge. The behavior of the aerodynamics performances from the MTE and the MLE should allow individual control of the morphing camber trailing and leading edges. The estimation of the performances of the morphing camber on an unmanned aerial vehicle indicates that the morphing of the camber allows a drag reduction. This result is due to the smaller angle of attack needed for an unmanned aerial vehicle equipped with the morphing camber system than an unmanned aerial vehicle equipped with classical aileron. In the case study, the morphing camber system was found to allow a reduction of the drag when the lift coefficient was higher than 0.48.

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