Withdrawal Notice: Design Optimization and Aerodynamic Analysis of a Hybrid Blended Wing Body-VTOL Unmanned Aerial Vehicle

2020 ◽  
Keyword(s):  
Design Optimization ◽  
Unmanned Aerial Vehicle ◽  
Aerodynamic Analysis ◽  
Aerial Vehicle ◽  
Blended Wing Body

Design, aerodynamic analysis and test flight of a bat-inspired tailless flapping wing unmanned aerial vehicle

2021 ◽  
Vol 112 ◽  
pp. 106557
Author(s):  
Dawei Bie ◽  
Daochun Li ◽  
Jinwu Xiang ◽  
Huadong Li ◽  
Zi Kan ◽  
...  
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Flapping Wing ◽  
Aerodynamic Analysis ◽  
Aerial Vehicle ◽  
Test Flight

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

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.

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

2011 ◽  
Author(s):  
Jean Koster ◽  
Claus-dieter Munz ◽  
Ewald Kraemer ◽  
Kee-Choon Wong ◽  
Dries Verstraete ◽  
...  
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Aerial Vehicle ◽  
Blended Wing Body

AERODYNAMIC OF UITM'S BLENDED-WING-BODY UNMANNED AERIAL VEHICLE BASELINE-II EQUIPPED WITH ONE CENTRAL VERTICAL RUDDER

2015 ◽  
Vol 75 (8) ◽  
Author(s):  
Wirachman Wisnoe ◽  
Rizal E.M. Nasir ◽  
Ramzyzan Ramly ◽  
Wahyu Kuntjoro ◽  
Firdaus Muhammad
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Cfd Simulation ◽  
Aerodynamic Characteristics ◽  
Control Surface ◽  
Wind Tunnel Experiments ◽  
Aerodynamic Parameter ◽  
Aerial Vehicle ◽  
Computational Fluid Dynamics Cfd ◽  
Blended Wing Body ◽  
Lift And Drag

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. 

Design Optimization, Modeling, and Control of Unmanned Aerial Vehicle Lifted By Coandă Effect

2017 ◽  
Vol 22 (3) ◽  
pp. 1327-1336 ◽  
Author(s):  
Hyunyong Lee ◽  
Seonhye Han ◽  
Hyoju Lee ◽  
Jaehyeok Jeon ◽  
Choonghan Lee ◽  
...  
Keyword(s):  
Design Optimization ◽  
Unmanned Aerial Vehicle ◽  
Coanda Effect ◽  
Optimization Modeling ◽  
Modeling And Control ◽  
Aerial Vehicle ◽  
Coandǎ Effect ◽  
And Control

Aero-structural numerical analysis of a blended wing body unmanned aerial vehicle using a jute-based composite material

2022 ◽  
Vol 49 ◽  
pp. 50-57
Author(s):  
Edgar Sarmiento ◽  
Carlos Díaz-Campoverde ◽  
José Rivera ◽  
Cristian Cruzatty ◽  
Edgar Cando ◽  
...  
Keyword(s):  
Composite Material ◽  
Numerical Analysis ◽  
Unmanned Aerial Vehicle ◽  
Aerial Vehicle ◽  
Blended Wing Body
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