Indian Journal of Science and Technology
Year: 2018, Volume: 11, Issue: 22, Pages: 1-7
U. Shiva Prasad1 *, S. Ajay Varma1 , R. Suresh Kumar2 , K. M. R. Sree Vaibhav1 and C. H. Satya Sandeep1
1 Institute of Aeronautical Engineering, Dundigal, Hyderabad – 500 043, Telangana, India; [email protected], [email protected], [email protected], [email protected]
2 Department of Aeronautical and Automobile Engineering, Manipal Institute of Technology, Manipal University, Manipal – 576104, Karnataka, India; [email protected]
*Author for correspondence
U. Shiva Prasad,
Institute of Aeronautical Engineering, Dundigal, Hyderabad – 500 043, Telangana, India; [email protected]
Objectives: The objective of this work is to investigate the flow over the truncated NACA2414 airfoil with slotted flap configuration. Investigation is carried using wind tunnel and commercial CFD tools with the consequences of the variation of speed, angle of attack of control surface and effective angle of attack. Methods/Statistical Analysis: Wind tunnel tests are performed on a reduced scale model (3:10) in wind tunnel at Manipal University. Experimentally determined static pressure distribution data at equal interval stations, placed over the wing are used to generate pressure data. The results obtained are used in turn as a benchmark to validate the CFD simulations. Findings: Findings clearly states that the blunt trailing edge has high drag coefficient. Although off set cavity and cavity has proven to be the ideal modification for trailing edge shape in a plane wing from the study. It can be concluded that the same is not true when such modifications are applied to slotted flap configuration. Application/Improvements: Further studies can be carried out with the alternative designs and a rigorous research can contribute in efficient designs in high lift devices.
Keywords: High-lift Devices, Numerical Analysis, Slotted Flaps, Truncated Airfoil, Wind Tunnel
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