An Investigation Into the Use of an Existing Shock Tube as a Driver for a Hypersonic Shock Tunnel
Abstract
This thesis describes experiments carried out using an existing tube alone, and with the tube connected to two-dimensional wedge nozzle. The range of maximum duration of steady reflected pressure from 3.5 to 5 milliseconds was achieved through tailored operation for incident shock strengths of 3.4 and 2.0, using pure Helium and a 70% Helium/30% Nitrogen mixture as the driver gas respectfully. Spark and continuous light shadowgraph techniques were attempted using an optical window at the Mach 4.3 location. Results demonstrated that the short duration flow phenomena in a shock tunnel can be recorded successfully using existing equipment. Calculations showed that the addition of a Mach 10 nozzle and 15 cu m (6' diameter x 15' long) dump chamber would provide a useful hypersonic facility for instruction and research.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1989
- Accession Number
- ADA208483
Entities
People
- Michael H. Sherman
Organizations
- Naval Postgraduate School