Experiments with a Supersonic Multi-Channel Radial Diffuser.
Abstract
A supersonic radial flow diffuser of the type to be used for high energy radial flow lasers was investigated in cold flow experiments. The diffuser consisted of a multitude of small channels and it was the main purpose of the investigations to optimize the geometry of these channels. The nominal inlet Mach number of the diffuser was 3.5 and its axial length-to-diameter ratio referred to the inlet was 0.5. The maximum pressure recovery rate obtained with this diffuser was 80% of normal shock recovery. Selected channels tested individually reached a recovery rate of over 100%. Failure of the diffuser as a whole to reach this performance must be attributed to flow instabilities triggered by flow irregularities inherent to the present radial flow system. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1980
- Accession Number
- ADA094192
Entities
People
- Howard L. Toms Jr
- Siegfried H. Hasinger
Organizations
- Wright Laboratory