ON SHOCK-TUNNEL SIMULATION OF SCRAMJET COMBUSTION CHAMBER PERFORMANCE
Abstract
The combustion-driven shock-tunnel can supply flows with the static temperatures, static pressures, and velocities required for simulation of scramjet combustion chamber conditions for flight Mach numbers up to 15. Limitations of the shock tunnel include the difficulty of attainment of a steady, equilibrium flow of pure air, free of driver gas contamination. In a British shock tunnel facility, a high speed sampling valve, probe, and gas analyzer were applied to the flow at the exit of a M = 3 nozzle, with stagnation pressure = 100 atmospheres and stagnation temperature = 6000 deg K, with coaxial hydrogen injection.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1968
- Accession Number
- AD0682127
Entities
People
- J. K. Richmond
- J. Swithenbank
- R. J. Parsons
Organizations
- Boeing