Computational Analysis of Fighter Aircraft Wing under Mach Number 0.7 for Small Sweep Angles

Abstract

Fighter aircraft wings are the leading lift generating components for any aerospace vehicle. The recital of any flying vehicle largely depends on its wing design. Missiles and the fighter aircrafts which are having propulsion system mostly have fins to control and maneuver. In this present paper work an attempt has been made to design a fighter aircraft wing configuration which will be used in some air launched air to surface guided weapons fighter aircraft. The main focus of this paper agreement in determining the Sweep-back effects on fighter aircraft wing under transonic condition at different angles of attack (AoA) from 0 to 5 degrees. For this the fighter aircraft wing performance for various flow conditions and sweep angles are obtained based on the empirical, semi-empirical and CFD simulation results. Hence by studying these computational results would help in the optimizing geometry for better performance, an finest wing design for the air launched air to surface body with conservative wing can be obtained.

In Tune with Times: Recent Developments in Theoretical, Experimental and Numerical techniques of Aircraft Engines

“…In past the studies conducted on inlet tone noise have focused only on linear waves and hence these studies are insufficient for studying the noise generated because of shock. The evolution of the shock system was studied here using method based on computational fluid dynamics [43], [53], [54]. Luc Reberga et al studied a military turbofan engine simulator and was aimed at describing the application of quasi-LPV modelling techniques to it.…”