Accession Number : ADA299820

Title :   Post Stall Control of Swept Wings,

Corporate Author : VIRGINIA POLYTECHNIC INST AND STATE UNIV BLACKSBURG

Personal Author(s) : Telionis, Demetri

PDF Url : ADA299820

Report Date : 1995

Pagination or Media Count : 85

Abstract : The work conducted on this effort is described in detail in six papers which were presented at various meetings. Copies of the papers are attached to this report. A brief description of this material is provided below. At the beginning of this effort, the fundamental character of the flow was investigated. In the first publication generated, we discuss the transient flow field over a delta wing during pitch-up motions to very large angles of attack. Emphasis was directed at the growth and the eventual breakdown of leading edge vortices.

Descriptors :   *SWEPT WINGS, *STALLING, CONTROL, ANGLES, MODELS, VORTICES, LEADING EDGES, FLOW, DELTA WINGS.

Subject Categories : Military Aircraft Operations
      Aircraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE