Accession Number:

ADP007704

Title:

Aerothermodynamics of Nozzle Flows for Advanced Hypersonic Propulsion Systems,

Descriptive Note:

Corporate Author:

MESSERSCHMITT-BOELKOW-BLOHM G M B H MUNICH (GERMANY F R)

Personal Author(s):

• Weiland, C.
• Hartmann, G.
• Menne, S.

Report Date:

1992-02-01

Pagination or Media Count:

11.0

Abstract:

One of the major tasks for the development of novel airbreathing space transportation systems, operating from usual airports by horizontal take off and landing, is the integration of an advanced propulsion system in the cell of that spacecraft. The air intake and in particular the free expansion nozzle affect not only the efficiency of the engine but also severely the forces and moments, and with that the control, of the complete spacecraft. Therefore, of course, it is necessary to know in detail the flow fields through such nozzles and its interaction with the external airflow. Another project deals with conventional rocket motor nozzles where by injection of turbine exhaust gases in the expansion part of the nozzle the wall of the nozzle is cooled film-cooling concept and the thrust is slightly increased.

Descriptors:

• *AIR BREATHING ENGINES(UNCONVENTIONAL)
• *HYPERSONIC FLOW
• *SPACE PROPULSION
• AIR
• AIR INTAKES
• AIRPORTS
• CELLS
• CONTROL
• EFFICIENCY
• ENGINES
• EXHAUST GASES
• EXPANSION
• EXTERNAL
• FLOW
• FLOW FIELDS
• INJECTION
• INTEGRATION
• INTERACTIONS
• LANDING
• MOMENTS
• MOTORS
• NOZZLES
• PROPULSION SYSTEMS
• ROCKET ENGINES
• ROCKETS
• SPACE TRANSPORTATION
• SPACECRAFT
• THRUST
• TRANSPORTATION
• TURBINES
• WALLS

Subject Categories:

• Fluid Mechanics
• Air Breathing Engines (Unconventional)
• Astronautics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE