Computational Study of Submerged Air Inlet Performance Improvement Using Vortex Generators

Abstract

In this computational work, the influence of a delta wing vortex generator on the boundary layer that develops upstream of a submerged air intake is studied. The state-of-the-art analysis and design of these intakes is discussed in detail. The flow in a conventional NACA inlet is analyzed numerically and its results are considered as a reference for the cases in which the vortex generator is included. A delta wing vortex generator is designed and mounted to the conventional NACA inlet, and the result of this configuration is studied through parametric variations of the vortex generator geometry. Finally, a support mast of the vortex generator is designed and included in the model, and simulations are performed for the configuration NACA inlet with vortex generator and mast. Three sideslip angles are considered for the mast. The results show that the use of the delta wing vortex generator is responsible for considerable reductions of the boundary-layer thickness and, consequently, significant improvements of the performance parameters of the NACA inlet. The improvements relative to the conventional NACA intake in terms of ram-recovery ratio and mass flow rate are of up to 53 and 19%, respectively.