Abstract Views :191 |
PDF Views:0
Authors
Affiliations
1 Institute of Aeronautical Engineering, Dundigal, Hyderabad – 500 043, Telangana, IN
2 Department of Aeronautical and Automobile Engineering, Manipal Institute of Technology, Manipal University, Manipal – 576104, Karnataka, IN
Source
Indian Journal of Science and Technology, Vol 11, No 22 (2018), Pagination: 1-7
Abstract
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.
Full Text
References
- Baker JP, Dam CPV. Drag Reduction of Blunt Trailing – Edges Airfoils. BBAA VI International colloquium on: Bluff bodies Aerodynamics and Applications Milano. Italy; 2008 Jul. p. 1–7.
- Dam V, Kahn LD, Berg ED. Trailing Edge Modifications for Flat back Airfoils. SANDIA REPORT. Unlimited Release; 2008. p. 1–22.
- Prasad US, Ajay VS, Rajat RH, Samanyu S. Aerodynamic Analysis over Double Wedge Airfoil IOP Conference Series: Materials Science and Engineering; 2017. p. 1–6. Crossref.
- Prabhar A, Ohri A. CFD analysis on MAV NACA 2412 wing in high lift take-off configuration for enhanced lift generation, Aeronautics and Aerospace Engineering. 2013; 2(5):1–8.
- Lavicka D, Matas R. Computation of drag and lift coefficients from simple two-dimensional objects with Reynolds number Re = 42,000. EDP Sciences; 2012. p. 1–6.
