Supersonic Combustion, Air Dissociation through Shock Waves and Aerodynamics of Chemically Reacting Gases in a Planar Converging - Diverging Nozzles.
Abstract
Much research has been accomplished to develope a supersonic ramjet engine. Very little headway has been made in theoretical design techniques as many of the standard computational methods used for ramjet subsonic combustion do not apply. For instance, it is possible to use a constant area nozzle for subsonic combustion in a ramjet as heat addition and frictional effects in the combustion chamber will decrease the pressure and accelerate the flow. For supersonic combustion the velocity decreases tending to choke the flow. To overcome this area increase in the combustion zone is used. A strong normal shock on the diffuser inlet for free stream mach numbers of 5 and 10 and the shock free flow of these mach numbers are assumed. Accompanied with the strong normal shock are large stagnation pressure losses in the diffuser inlet, meaning the diffuser inlet will act as a flat plate to oncoming airflow. For this reason, it would be best to provide air spillage and not use too large an inlet. The final Thrust Specific Fuel Comsumption values are sufficiently high to warrant further investigation into supersonic combustion as a method of propulsion.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1979
- Accession Number
- ADA073135
Entities
People
- Dennis W. Schroll