Performance investigation of a finite wing section with bleed hole allowing boundary layer suction with different locations & areas of exit

• Main Authors: Mishra, Nirmith Kumar, Kammela, Sai Vamsi, Bade, Shashank, Annem, Suhas Chandra, Pusika, Naveen
• Format: Conference Proceeding
• Language: English
• Subjects: Angle of attack; Boundary layer flow; Data processing; Ducts; Flow control; Momentum transfer; Suction
• ISSN: 0094-243X; 1551-7616
• DOI: 10.1063/5.0113353

The aim of this study is to find the optimal location and area of exit for the boundary layer suction control parameter. A computational study is carried over a finite wing section to improve the aerodynamic performance by controlling the boundary layer flow. A boundary layer suction flow control mechanism is used to allow the free stream flow to pass through the duct from leading edge to an arbitrary location along chord on the surface of the finite wing section at various locations respectively. This study is carried out on the wing section with a constant inlet duct area, varying areas and locations of duct outlets. The arbitrary locations of outlet are considered at 0.75%c, 0.625%c, 0.5%c, 0.375%c, 0.25%c for 0o, 2.5o, 5o, 7.5o, 10o angles of attack and outlet locations with the respective inflation points for 0o, 2.5o, 5o, 7.5o, 10o angles of attack respectively are included. Different positions of exit varying along the chord of the airfoil are considered with respect to the angle of attack to come up with the optimal area and location of exit. These ducts are shaped as converging, diverging and constant area ducts to study the varying momentum transfer into the boundary layer and their effects on aerodynamic efficiency. The study involves the use of XFLR 5, Ansys for analysis and MATLAB for the data processing and featuring.