Accession Number:

AD0275463

Title:

SECONDARY GAS INJECTION IN A CONICAL ROCKET NOZZLE. 1. EFFECT OF ORIFICE DIAMETER AND MOLECULAR WEIGHT IN INJECTANT

Descriptive Note:

Corporate Author:

JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB

Personal Author(s):

• Walker, R. E.
• Stone, A. R.
• Shandor, M.

Report Date:

1962-02-01

Pagination or Media Count:

56.0

Abstract:

Data are presented on interference forces resulting when a gas at ambient temperature is laterally injected through a single circular orifice in the conical portion of a rocket nozzle into hot supersonic propellent gases. Variables examined are injectant orifice size and associated pressure ratio change and effect of injectant molecular weight and specific heat ratio. Other parameters remain essentially constant during these tests. Simple theoretical arguments can predict relative effects of intrinsic injectant properties, but pressure ratio effects are not adequately described. Effectiveness of secondary injection depends on injectant orifice size, which was not treated in any theoretical modes.

Descriptors:

• *CONTROL
• *EXHAUST GASES
• *CONTROL SYSTEMS
• *MOLECULAR WEIGHT
• *NITROGEN
• *HYDROGEN
• *MATHEMATICAL ANALYSIS
• *PRESSURE
• *HELIUM
• *CARBON DIOXIDE
• *INJECTORS
• *INJECTION
• *CONICAL NOZZLES
• *ORIFICES
• *THRUST
• *SPECIFIC HEAT
• *SPECIFIC IMPULSE
• *ROCKET NOZZLES
• THRUST VECTOR CONTROL SYSTEMS
• SECONDARY INJECTION
• ARGON

Subject Categories:

• Manufacturing and Industrial Engineering and Control of Production Systems

Distribution Statement:

APPROVED FOR PUBLIC RELEASE