An Experimental Study of Chin-Intakes for Airbreathing Missiles with High Agility
Herrmann, Dirk and Triesch, Klaus and Gülhan, Ali (2007) An Experimental Study of Chin-Intakes for Airbreathing Missiles with High Agility. Journal of Propulsion and Power, 24 (2), pp. 236-244. AIAA.
Full text not available from this repository.
The performance of three chin-intakes for airbreathing missiles with high agility has been investigated in a large maneuver range at supersonic speed. This experimental study is recovery and mass flow were discovered at angles of attack greater than 18°. To understand these effects in more details chin-intakes have been analyzed at a design Mach number of 3.0 at angles of attack ranging from -30° to 30° and at angles of sideslip ranging from -30° and 30° in the Trisonic Wind Tunnel. The results clearly show that boundary layer flow, vortices and flow sepration are responsible for the losses of pressure recovery and mass flow. The subsequently added boundary layer bleed permits a better pressure recovery and a delay of the intake buzzing.
|Title:||An Experimental Study of Chin-Intakes for Airbreathing Missiles with High Agility|
|Journal or Publication Title:||Journal of Propulsion and Power|
|In ISI Web of Science:||Yes|
|Page Range:||pp. 236-244|
|Series Name:||Journal of Propulsion and Power|
|Keywords:||missiles, air breathing propulsion, high agility, ramjet performance|
|HGF - Research field:||Aeronautics, Space and Transport|
|HGF - Program:||Aeronautics|
|HGF - Program Themes:||L RR - Rotorcraft Research|
|DLR - Research area:||Aeronautics|
|DLR - Program:||L AR - Aircraft Research|
|DLR - Research theme (Project):||["eprint_fieldopt_dlr_project_search_L000" not defined]|
|Institutes and Institutions:||Institute of Aerodynamics and Flow Technology|
|Deposited By:||Christine Adams|
|Deposited On:||26 Mar 2008|
|Last Modified:||15 Jan 2010 02:06|
Repository Staff Only: item control page