Accession Number : ADA332525

Title :   An Investigation of the Flowfleld for an Integrated Airframe/Propulsion System

Descriptive Note : Final rept. 1 Apr-30 Sep 97

Corporate Author : AIR FORCE ACADEMY COLORADO SPRINGS CO

Personal Author(s) : Kreins, Alois F.

PDF Url : ADA332525

Report Date : OCT 1997

Pagination or Media Count : 40

Abstract : This report results from a contract tasking USAFA/DFAN as follows: The contractor will modify an existing wind tunnel model of a hypersonic vehicle to incorporate devices that permit control of the onset of boundary layer transition. He will conduct comprehensive wind tunnel tests to determine the ct on the forebody flowfield of fixing the transition location.

Descriptors :   *FLOW FIELDS, *BOUNDARY LAYER TRANSITION, *HYPERSONIC FLOW, *AIRCRAFT DESIGN, AERODYNAMIC STABILITY, TURBULENT BOUNDARY LAYER, ANGLE OF ATTACK, FLOW VISUALIZATION, WIND TUNNEL TESTS, FREE STREAM, REYNOLDS NUMBER, HYPERSONIC WIND TUNNELS, LIFT TO DRAG RATIO.

Subject Categories : Aerodynamics
      Military Aircraft Operations

Distribution Statement : APPROVED FOR PUBLIC RELEASE