Aerodynamic Performance of an Injector Strut for a Round Scramjet Combustor (Postprint)
Abstract
Numerical studies were performed to examine different strut configurations to determine their mixing characteristics for possibly use with fuel-injector ports for round scram jet-combustor applications. Several strut configurations were tested to provide a better understanding of the flow physics, in terms of pressure, total pressure recovery, vorticity magnitude, streamlines, and velocity vectors. The conceptual strut designs were placed in a rectangular flow path, and the computations will be followed by an experimental program in the AFRL/RZA Research Cell 19 supersonic wind-tunnel facility, which has a rectangular cross-section area of 12.7 cm x 15.24 cm. The struts were sized, however, for eventual use in a 25.4 cm (10-inch) round combustor. The strut with a constant leading-edge angle and a moderately swept trailing edge seems to provide reasonably good mixing flow features without significantly compromising the total pressure recovery.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 2007
- Accession Number
- ADA479623
Entities
People
- Charbel N. Raffoul
- Chung-jen Tam
- Kuang-yu Hsu
- Mark R. Gruber
Organizations
- Air Force Research Laboratory