Flow Separation Within the Engine Inlet of an Uninhabited Combat Air Vehicle (UCAV)-Reference-Cited by-同舟云学术

Flow Separation Within the Engine Inlet of an Uninhabited Combat Air Vehicle (UCAV)

Published:2004-03-01 Issue:2 Volume:126 Page:266-272
ISSN:0098-2202
Container-title:Journal of Fluids Engineering
language:en
Short-container-title:

Author:

Brear Michael J.¹,Warfield Zachary²,Mangus John F.³,Braddom Steve⁴,Paduano James D.⁵,Philhower Jeffry S.³

Affiliation:

1. Department of Mechanical and Manufacturing Engineering, University of Melbourne, Australia

2. Structures and Configuration Group, Mechanical Engineering Section, Jet Propulsion Laboratory

3. Integrated Systems, Northrop Grumman Corporation

4. Department of Civil & Mechanical Engineering, West Point

5. Gas Turbine Laboratory, Massachusetts Institute of Technology

Abstract

This paper discusses the structure of the flow within the engine inlet of an uninhabited combat air vehicle (UCAV). The UCAV features a top-mounted, serpentine inlet leading to an engine buried within the fuselage. The performance of the inlet is found to depend strongly on a flow separation that occurs within the inlet. Both the time-averaged and the unsteady structure of this separation is studied, and an argument relating the inlet performance to the behavior of this separation is suggested. The results presented in this paper also suggest that there are considerable aerodynamic limitations to further shortening or narrowing of the inlet. Since there are substantial, system level benefits from using a smaller inlet, the case for separated flow control therefore appears clear.

Publisher

ASME International

Subject

Mechanical Engineering

Link

http://asmedigitalcollection.asme.org/fluidsengineering/article-pdf/126/2/266/5541606/266_1.pdf

Reference16 articles.

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3. Ng, W., and Burdisso, R. A., 2001, “Active acoustic and flow control for aeropropulsion,” 39th AIAA Aerospace Sciences Meeting & Exhibit, Reno, AIAA paper no. AIAA 2001-0220.

4. SAE Committee S-16, 1977, “ARP 1420-Gas turbine engine inlet flow distortion guidelines.”

5. Warfield, Z., 2001, “Active control of separation induced distortion in a scaled tactical aircraft inlet,” M.S. Thesis, Massachusetts Institute of Technology.

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