Experimental aerodynamics of Blended Wing Body (BWB) Unmanned Aerial Vehicle (UAV) with elevator deflection of +15° and -15° using wind tunnel (Mach number 0.1-0.15) / Wan Mohd Hafizan Wan Razali

This thesis presents a study of aerodynamic of a Blended Wing Body (BWB) Unmanned Aerial Vehicle (UAV) with elevator deflection +15° and -15° using wind tunnel. This project is the continuation of previous research using Low Speed Tunnel LST and Computational Fluids Dynamics (CFD) simulation and is...

Full description

Saved in:
Bibliographic Details
Main Author: Wan Razali, Wan Mohd Hafizan
Format: Thesis
Language:English
Published: 2009
Subjects:
Online Access:https://ir.uitm.edu.my/id/eprint/36061/1/36061.pdf
Tags: Add Tag
No Tags, Be the first to tag this record!
Description
Summary:This thesis presents a study of aerodynamic of a Blended Wing Body (BWB) Unmanned Aerial Vehicle (UAV) with elevator deflection +15° and -15° using wind tunnel. This project is the continuation of previous research using Low Speed Tunnel LST and Computational Fluids Dynamics (CFD) simulation and is very important to validate the result it. This project will present the Analysis of BWB Aerodynamics at low subsonic speed. The study will focus on the aerodynamic characteristics at various angles of attack at 0.1 Mach number using wind tunnel test. The objective of this project is to obtain the aerodynamic characteristics such as lift coefficient, drag coefficient and pitching moment coefficient of Blended Wing Body (BWB) Unmanned Aerial Vehicle (UAV) with elevator deflection +15° and -15° using wind tunnel and also to observe the quality of flow pattern around the BWB UAV at various angles of attack using flow visualization techniques.