TY - JOUR
T1 - Numerical analysis of the effect of vortex control mechanism on longitudinal aerodynamics of lifting body
AU - Badarudin Mohamad Badry, Ahmad
AU - Lee, Yin Jen
AU - Chong, Wen Tong
AU - Nik-Ghazali, Nik Nazri
AU - Oon, Cheen Sean
AU - Salim Newaz, Kazi
N1 - Funding Information:
The authors gratefully acknowledge Ministry of Higher Education, Malaysia and University of Malaya for financial support through the High Impact Research Grant UM.C/625/1/HIR/MOHE/ENG/46 , UMRG grant RP006B-13AET and FRGS grant FP062/2010A . The authors would also like to thank the staff of Universiti Teknologi Malaysia, Skudai, Malaysia for technical support to conduct this research work.
Copyright:
Copyright 2013 Elsevier B.V., All rights reserved.
PY - 2013/10
Y1 - 2013/10
N2 - A numerical analysis was carried out on the aerodynamics of a lifting body consisting of a blunted, half-cone geometry. In the present paper, the application of a novel vortex control mechanism in the form of leading-edge rotating cylinders, to alter lift, drag and pitching properties, were performed. For the first time, the use of rotating cylinders to manipulate the swirling vortices above the lifting body for pitch control is reported. This study focuses on flight conditions pertaining to the landing phase. The unsteady Reynolds-Averaged Navier-Stokes (URANS) method for flow simulation is verified and compared with wind-tunnel test. Simulation of lifting body performance is carried out at varying angles of attack with different directions of cylinder rotation and rotation speeds. Leading-edge vortices similar to those formed on delta-wings are observed. Rotating cylinders are shown to be an effective method of controlling the leading-edge vortices. Momentum injection by rotating the cylinders in the direction of the flow can suppress formation of vortices, reducing the lift force, drag force and pitching moment of the lifting body. Rotating in the opposite direction strengthens the vortices, increasing the lift force, drag force and pitching moment. Rotating cylinders are found to offer limited pitch control; regardless, the lifting body studied remains inherently unstable in pitch mode.
AB - A numerical analysis was carried out on the aerodynamics of a lifting body consisting of a blunted, half-cone geometry. In the present paper, the application of a novel vortex control mechanism in the form of leading-edge rotating cylinders, to alter lift, drag and pitching properties, were performed. For the first time, the use of rotating cylinders to manipulate the swirling vortices above the lifting body for pitch control is reported. This study focuses on flight conditions pertaining to the landing phase. The unsteady Reynolds-Averaged Navier-Stokes (URANS) method for flow simulation is verified and compared with wind-tunnel test. Simulation of lifting body performance is carried out at varying angles of attack with different directions of cylinder rotation and rotation speeds. Leading-edge vortices similar to those formed on delta-wings are observed. Rotating cylinders are shown to be an effective method of controlling the leading-edge vortices. Momentum injection by rotating the cylinders in the direction of the flow can suppress formation of vortices, reducing the lift force, drag force and pitching moment of the lifting body. Rotating in the opposite direction strengthens the vortices, increasing the lift force, drag force and pitching moment. Rotating cylinders are found to offer limited pitch control; regardless, the lifting body studied remains inherently unstable in pitch mode.
KW - Computational fluid dynamics
KW - Lifting body
KW - Moving surface boundary layer control
KW - Vortex control
UR - http://www.scopus.com/inward/record.url?scp=84885173923&partnerID=8YFLogxK
U2 - 10.1016/j.ast.2013.08.007
DO - 10.1016/j.ast.2013.08.007
M3 - Article
AN - SCOPUS:84885173923
VL - 30
SP - 232
EP - 238
JO - Aerospace Science and Technology
JF - Aerospace Science and Technology
SN - 1270-9638
IS - 1
ER -