Surface Pressure Distribution of a Flapped-Airfoil for Different Momentum Injection at the Leading Edge
The aim of the research work is to modify the NACA 4215 airfoil with flap and rotary cylinder at the leading edge of the airfoil and experimentally study the static pressure distribution over the airfoil completed with flap and leading-edge vortex generator. In this research, NACA 4215 wing model has been constructed by generating the profile geometry using the standard equations and design software such as AutoCAD and SolidWorks. To perform the experiment, three wooden models are prepared and tested in subsonic wind tunnel. The experiments were carried out in various angles of attack. Flap angle and momentum injection rate are changed to observe the characteristics of pressure distribution. In this research, a new concept of flow separation control mechanism has been introduced to improve the aerodynamic characteristics of airfoil. Control of flow separation over airfoil which experiences a vortex generator (rotating cylinder) at the leading edge of airfoil is experimentally simulated under the effects of momentum injection. The experimental results show that the flow separation control is possible by the proposed mechanism, and benefits can be achieved by momentum injection technique. The wing performance is significantly improved due to control of flow separation by momentum injection method.
Digital Object Identifier (DOI): doi.org/10.5281/zenodo.2643638Procedia APA BibTeX Chicago EndNote Harvard JSON MLA RIS XML ISO 690 PDF Downloads 376
 A. L. Braslow, A history of suction-type laminar-flow control with emphasis on flight Research, Monographs in Aerospace History #13, NASA History Division Office of Policy and Plans, NASA Headquarters Washington, DC 205469,1999.
 A. Seifert, T. Bachar, D. Koss, M. Shepshelovich, and I. Wygnanski, Oscillatory blowing: A tool to delay boundary-layer separation, AIAA Journal, 31(11), 1993.
 L. M. M. Boermans, Glide ratio 1:80, A solar challenge?, Paper at XXV OSTIV Congress St. Auban, France, 1997.
 J. Little, M. Nishihara, I. Adamovich, and M. Samimiy. Separation control from the flap of a high-liftairfoil using DBD plasma actuators. In AIAA Paper 2009 145, 2009.
 John D. Anderson Jr Fundamentals of Aerodynamics., 5th Edition, Mc-Graw Hill, December 2009.
 John D. Anderson Jr. (2012), Introduction to Flight, 7th Edition, Mc-Graw Hill, August 2011.