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Aerodynamic Design and Exploration of a Blended Wing Body Aircraft at Subsonic Speed

Dakka, Sam; Johnson, Oliver

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Authors

SAM DAKKA Sam.Dakka@nottingham.ac.uk
Assistant Professor

Oliver Johnson



Abstract

Blended Wing Body (BWB) is a novel aircraft concept which provides many different aerodynamic benefits over conventional aircrafts design. This research investigated the BWB design, L/D characteristics, surface pressure distribution and span-wise lift distribution of a BWB aircraft at low to medium subsonic speeds. A BWB model was designed, manufactured and tested in a subsonic wind tunnel to validate the CFD simulation. The results gained from the investigation proved that BWB has a L/D improvement of 9.4% than conventional aircrafts and 21% increase at medium subsonic speeds (Mach 0.6) compared to lower subsonic speeds of 25 m/sec. It was found that the lift minimally increases between the two speeds; however the improvement is generated due to drag reduction. The drag reduction is accomplished due to boundary layer attachment for a longer period of time before separation occurs. It is this difference which generates the lift to drag ratio improvement.

Citation

Dakka, S., & Johnson, O. (2019). Aerodynamic Design and Exploration of a Blended Wing Body Aircraft at Subsonic Speed. International Journal of Aviation, Aeronautics, and Aerospace, 6(5),

Journal Article Type Article
Acceptance Date Nov 17, 2019
Online Publication Date Nov 27, 2019
Publication Date Nov 27, 2019
Deposit Date Nov 28, 2019
Publicly Available Date Mar 28, 2024
Journal International Journal of Aviation, Aeronautics and Aerospace
Electronic ISSN 2374-6793
Publisher Embry-Riddle Aeronautical University
Peer Reviewed Peer Reviewed
Volume 6
Issue 5
Article Number 17
Keywords Aerodynamics, Blended Wing Body, Wind Tunnel testing, Computational Fluid Mechanics
Public URL https://nottingham-repository.worktribe.com/output/3433765
Publisher URL https://commons.erau.edu/ijaaa/vol6/iss5/17
Additional Information Scholarly Commons © 2019

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