Numerical Analysis of Role of Bumpy Surface to Control the Flow Separation of an Airfoil

• DOI: 10.1016/j.proeng.2014.11.846
• Publication Date: 2014-12-27T13:00:49Z
• Authors: Syed Hasib Akhter...; Md. Abdullah Al Bari; Md Emran; Ahsan Ferdaus
• Keywords: NACA airfoil; Trailing edge; Lift (data mining); Flow Control; Separation (statistics)

The efficiency of mission varying aircrafts can be altered by either flow control method or adaptive wing technology. Here we have researched the separation airfoil providing partial bumpy on upper surface geometry. Flow low speed is considered. For analysis purpose NACA 4315 was chosen. Two models were generated (i) regular using profile (ii) trailing edge at 80%C. Numerical approach undertaken to observe aerofoil. From observation it noted that aerofoil delayed. occurs 9 degree angle attack in smooth whereas 15 attack. Thus, indicating increase lift force and an due surface.