Bump type supersonic intake design for air vehicles

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Thesis Type: Postgraduate

Institution Of The Thesis: Gazi University, Fen Bilimleri Enstitüsü, Turkey

Approval Date: 2023

Thesis Language: Turkish

Student: Oğuzhan ÇABUK

Supervisor: Nureddin Dinler

Open Archive Collection: AVESIS Open Access Collection

Abstract:

Different intake types are used in air-breathing jet powered supersonic aircraft to reduce the speed to subsonic speeds. In the design of intake for modern generation fighter, the type of intake known as "bump" or "diverterless" has gained prominence in the literature due to its superior characteristics in terms of weight, complexity, and radar visibility. In this thesis, the design and performance of bump type intake were investigated. First of all, numerical solution of conical shock for the bump type air intake design was realized and a code structure was created that will automatically create in the computer aided design environment by defining the surface design method. Bump surface performance was determined using computational fluid dynamics analyses. In this context, validation studies for computational fluid dynamics method using OpenFOAM-HISA solver and mesh independency studies were carried out. Computational fluid dynamics analyzes were performed to determine the performance of 8 different bump surfaces and 2 different cones used in the design of bump surfaces at design Mach number. As a result of the thesis, the shock structure and shock flow properties of the bump surface at supersonic design speed were compared with the conical shock and conical shock flow properties. It has been observed that the bump surface generates a shock that resembles the geometric structure of a conical shock and the flow properties at the end of the bump compression surface are close to the flow properties after the conical shock. It has also been observed that the pressure value decreases along the span of the surface from the symmetry axis on the bump surface, and therefore the boundary layer flow on the surface is diverted to the outside of the bump surface. An increase in the radial angle and cone angle, which are key design parameters of the bump compression surface, was observed to enhance the boundary layer divert capability of the surface.

Key Words : Intake, Bump, DSI, Supersonic Flow, Conical Shock, CFD, OpenFOAM