Open AccessSteady tangential control jet for improving the effectiveness of a rudder under one-engine inoperative condition
Author(s) -
P. Leelaburanathanakul,
V. Virangkur,
T. Wangsiripaisarn,
Jeerasak Pitakarnnop,
Asi Bunyajitradulya
Publication year - 2021
Publication title -
journal of physics. conference series
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.21
H-Index - 85
eISSN - 1742-6596
pISSN - 1742-6588
DOI - 10.1088/1742-6596/1733/1/012001
Subject(s) - rudder , drag , mechanics , drag coefficient , lift coefficient , control theory (sociology) , turbulence , flow control (data) , jet (fluid) , computational fluid dynamics , physics , mathematics , engineering , computer science , aerospace engineering , control (management) , reynolds number , telecommunications , artificial intelligence
The aim of the research is to numerically investigate the use of a steady tangential control jet (CJ) at the hinge of the vertical stabilizer as an active flow control (AFC) technique to improve the effectiveness of a rudder on a subsonic aircraft during one-engine inoperative (OEI) condition by keeping the flow attached to the control surface. The goals are in two folds: firstly to investigate the effects of CJ parameters, specifically the jet-to-freestream velocity ratio ( r V ) and the jet slot height ratio ( r H ), on the vertical stabilizer performance, and secondly to find the optimum CJ condition that yields the improved and optimal performance. In this regard, the optimal condition of the CJ is prescribed as the condition that gives the maximum side force to drag ratio under the requirements that the required minimum trim side force can be achieved and there is an improvement in control surface margin for yawing motion. The investigation is carried out through computational fluid dynamics (CFD) using the Spalart-Allmaras turbulent model. Under the optimal CJ condition, its implementation can provide the required minimum rudder side force coefficient ( C y, trim ) of 1.19 at a rudder drag coefficient ( C d ) of 0.0013, a decrease in drag coefficient of 95% over the baseline case of plain flap without CJ. In addition, there is an improvement in rudder margin with the maximum side force coefficient increase by 42%, and the corresponding drag force coefficient decrease by 25% for the aircraft to yaw in a direction of the still-active engine.