Accession Number:

ADA455544

Title:

An Experimental Investigation of Thrust Vector Control by Secondary Injection

Descriptive Note:

Contract rept.

Corporate Author:

PURDUE UNIV LAFAYETTE IN

Personal Author(s):

• Guhse, Richard D.

Report Date:

1965-09-01

Pagination or Media Count:

124.0

Abstract:

An experimental investigation was conducted to examine the flow field produced when a secondary gas is injected into a supersonic primary stream. A preliminary analytical investigation revealed that several parameters such as the primary and secondary gas properties, flow conditions and geometrical parameters were influential in determining the nature of the flow field produced by secondary injection and the resulting side force. The investigation reported herein is concerned with the results of a systematic variation of these parameters. Experiments were conducted in a Mach 2.0, two-dimensional blow down wind tunnel utilizing air as the primary and secondary gases. The secondary gas was injected through a rectangular slot extending the width of the primary nozzle. The area of the slot was varied from 12 to 10 of the primary nozzle throat area in five increments. For each value of slot area the secondary to primary stagnation pressure ratio was varied from 0.301 to 1.175 in six increments. The experiments were conducted for injection normal to the nozzle axis and at an angle of 10 degree upstream of this normal at an axial position where the primary Mach number was 1.90. In each case preliminary diagnostic investigations optical were conducted to determine the nature of the flow field.

Descriptors:

• *THRUST VECTOR CONTROL SYSTEMS
• *SECONDARY INJECTION
• GASES
• FLOW FIELDS
• NOZZLE THROATS
• MACH NUMBER

Subject Categories:

• Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE