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

Nornashiha Mohd Saad,Zurriati Mohd Ali,Ehan Sabah Shukri Askari,Wirachman Wisnoe,Rizal Effendy Mohd Nasir,P Tandon,R Furutani,W Wisnoe

doi:10.1051/matecconf/201925602004

Abstract

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.

Highlights

Blended Wing Body (BWB) aircraft is tailless design that combined wing and fuselage [1, 2]
This paper aims to analyse the aerodynamic characteristics of Blended Wing Body–Unmanned Aerial Vehicle (BWB-UAV) equipped with horizontal stabilizer at different locations and sizes
The aerodynamic characteristics of Universiti Teknologi Mara (UiTM) BWB-UAV Prototype have been presented in terms of lift, drag and pitching moment coefficients

Summary

Introduction

Blended Wing Body (BWB) aircraft is tailless design that combined wing and fuselage [1, 2]. BWB is usually better in terms of aerodynamic performance, lower fuel burn and lower noise emission [3]. Reduction of maximum takeoff weight (MTOW) by 15% and reduction of fuel burn per seat by 28% lower the operating cost of BWB [4]. BWB increases range and payload capacity with 27% reduction in fuel burn per seat [5]. BWB concept can save up to 30% of fuel consumption by improving the lift-to-drag ratio [6]. There are some issues in BWB related to aerodynamic, structures and control [2]

Objectives

Results

Conclusion