Effect of Plain Flap Over the Aerodynamic Characteristics of Airfoil NACA 66-015

Authors : Imanbir Singh.

Volume/Issue : Volume 2 - 2017, Issue 6 - June

Google Scholar : https://goo.gl/JsqUwj

Scribd : https://goo.gl/jaCHPv

Thomson Reuters ResearcherID : https://goo.gl/3bkzwv

Effect of plain flap on the distribution over the symmetrical aerofoil NACA 66 015. Flap is a sub-control surface that enhances the lift of the aircraft. This paper includes placing of NACA 66-015 aerofoil with trailing edge flaps at a constant Reynolds number. Measurement of coefficient of pressure (Cp) over the aerofoil at different angle of attacks, different flap settings have been done. An investigation on performance of aerofoil with flap has been done to understand the pressure distribution over and below the wing. Laser illuminated smoke visualization have been used to identify flow separation point. It was observed that the stall angle increased and performance of the wing was more enhanced as the angle of attack increased. ANSYS FLUENT analysis to validate experimental results.


Paper Submission Last Date
31 - May - 2023

Paper Review Notification
In 1-2 Days

Paper Publishing
In 2-3 Days

Video Explanation for Published paper

Never miss an update from Papermashup

Get notified about the latest tutorials and downloads.

Subscribe by Email

Get alerts directly into your inbox after each post and stay updated.

Subscribe by RSS

Add our RSS to your feedreader to get regular updates from us.