Accession Number:

AD0839274

Title:

FLEXIBLE EXIT CONE NOZZLE DEVELOPMENT PROGRAM. VOLUME 2. COLD FLOW TESTS

Descriptive Note:

Final rept. 15 Mar 1967-31 Jul 1968 on Phase 2

Corporate Author:

MORTON THIOKOL INC BRIGHAM CITY UT WASATCH OPERATIONS

Personal Author(s):

Report Date:

1968-08-01

Pagination or Media Count:

95.0

Abstract:

This report documents the cold flow testing conducted on the flexible exit cone nozzle. The cold flow program was conducted to establish the performance characteristics of the Flex-X nozzle. The influence of various geometric parameters on nozzle side force, actuation torque, and axial thrust were investigated. The flexible exit cone nozzle turns the gas in the supersonic portion of the nozzle. With proper design this concept can produce side forces greater than those realized with conventional vector nozzle systems. The maximum side force amplification achieved in this program was approximately 1.65 on the 101 expansion ratio nozzle and 1.95 on the 251 expansion ratio nozzle. Torque amplifications were 3.6 and 2.9 respectively. Axial thrust losses for these configurations were from one to two percent. The maximum thrust loss measured was approximately eight percent. Between five and ten degrees nozzle vector, the compression side shock intersected the expansion wall and moved into the nozzle far enough to cause a decrease in side force amplification. Where high vector angles are required, the seal could be moved aft to prevent this shock intersection.

Subject Categories:

  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE