EFFECT OF SPIKES INTEGRATED TO AIRFOIL AT SUPERSONIC SPEED

Md Akhtar Khan, Karrothu Vigneshwara, Suresh Kukutla, Avinash Gupta

Abstract: The objective of this is to analyse the flow field over an aerofoil section integrated with spikes at supersonic speed (Mach number greater than 1). Use of spike integrated with aerofoil changes the flow characteristics over aerofoil and hence aerodynamic lift and drag. The experiment consists of flow visualization graphs and measurement of coefficient of aerodynamic drag and lift. Here we are using different shapes of spike like sharp edge and hemi spherical edge. In this we will compare the flow over aerofoil with spike and without spike. The flow analysis is done by using Computational fluid dynamics (CFD). CFD is the study of external flow over a body or internal flow through the body. CFD is aiding aero-dynamist to better understand the flow physics and in turn to design efficient models. In short, CFD is playing a strong role as a design tool as well as a research tool.

Keywords: NACA 651-412 airfoil, spike, Ansys Fluent, Ansys ICEM CFD, Pressure Coefficient

DOI: https://doi.org/10.15623/ijret.2014.0310035