John D. Mack

Date of Award

6-2005

Document Type

Thesis

Degree Name

Master of Science

Department

Department of Aeronautics and Astronautics

First Advisor

Miltion E. Franke, PhD

Abstract

The purpose of this study was to create and investigate starting techniques aimed at allowing complex, three-dimensional, inward-turning inlets to start by swallowing the shock wave associated with unstarted inlets. The techniques are rooted in supersonic diffuser theory and the Kantrowitz limit; they attempt to alleviate the over contraction that occurs in inward-turning inlets at flight speeds below the on-design Mach number. Five cases, three geometries at two flow conditions and the base non-modified inlet at the two flow conditions, were generated, and all were numerically simulated using a commercially produced numerical solver: CFD++. The simulations were computed using the inviscid Navier-Stokes/Euler equations in a steady state analysis to generate the shock wave, followed by a transient analysis to allow the shock to move in time. The results of the investigation show that all five cases proved to be sub-optimal, as none were able to successfully swallow the shock during the transient simulation. However, the results from this analysis indicate that the slit case, designs that extend the initial spill areas of the inlet, appear to hold the most potential in the creation of a successful starting technique. The slit case holds the most potential because the slit Mach 2.7 case was just as effective as the slot Mach 2.7 case, yet the slit area was half the size as the designed slots. Future research should attempt to characterize the effects of slits at different Mach numbers and at various complexities of inlet and slit geometry.

AFIT Designator

AFIT-GAE-ENY-05-J07

DTIC Accession Number

ADA438398

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