A blended wing body airplane with a close-coupled, tilting tail

4th AEROTECH- Innovation in Aerospace Engineering and Technology

航空航天工程

Nasir, R.E.M.^1 ; Mazlan, N.S.C.^1 ; Ali, Z.M.^1 ; Wisnoe, W.^1 ; Kuntjoro, W.^1

Aviation Technology Research (ATR) Group, Flight Tech. and Test Centre (FTTC), Faculty of Mech. Engr. Universiti Teknologi Mara, Malaysia^1

关键词: Blended wing body;    Blended wing body aircrafts;    Lift to drag ratio;    Roll stability;    Sideslip angles;    Static stability;    Trailing edges;    Wind tunnel experiment;   

Others  :  https://iopscience.iop.org/article/10.1088/1757-899X/152/1/012021/pdf
DOI  :  10.1088/1757-899X/152/1/012021

学科分类：航空航天科学

来源: IOP

【 摘 要 】

This paper highlights a novel approach to stabilizing and controlling pitch and yaw motion via a set of horizontal tail that can act as elevator and rudder. The tail is incorporated into a new design of blended wing body (BWB) aircraft, known as Baseline-V, located just aft of the trailing edge of its inboard wing. The proposed close-coupled tail is equipped with elevators that deflect in unison, and can tilt - an unusual means of tilting where if starboard side is tilted downward at k degree, and then the portside must be tilted upward at k degree too. A wind tunnel experiment is conducted to investigate aerodynamics and static stability of Baseline-V BWB aircraft. The model is being tested at actual flight speed of 15 m/s (54 km/h) with varying angle of attack for five elevator angle cases at zero tilt angle and varying sideslip angle for four tilt angle cases at one fixed elevator angle. The result shows that the aircraft's highest lift-to-drag ratio is 32. It is also found that Baseline-V is statically stable in pitch and yaw but has no clear indication in terms of roll stability.