Accession Number:

AD0489063

Title:

EXPLORATORY INVESTIGATION OF THE EFFECT OF RING TAILS ON THE JET-ON BASE PRESSURE OF A BODY OF REVOLUTION OF FREE-STREAM MACH NUMBERS OF 2.5 AND 3.0,

Descriptive Note:

Corporate Author:

ARMY MISSILE RESEARCH DEVELOPMENT AND ENGINEERING LAB REDSTONE ARSENAL AL AER OBALLISTICS DIRECTORATE

Personal Author(s):

• Rubin, Donald V.

Report Date:

1966-07-05

Pagination or Media Count:

46.0

Abstract:

The influence of a secondary flow field on the jet-on and jet-off base pressure of a six-caliber ogive cylinder was investigated. The results of this investigation indicate that body base drag can be reduced by favorable interference for both the jet-on and jet-off cases. The data presented are based on the results of an exploratory wind tunnel test made at Mach numbers 2.5 and 3.0. The test model had a nozzle-to-base diameter ratio of 0.2. The jet was simulated by air, and the secondary flow field was generated by ring configurations. Ring parameters varied in the test were longitudinal position, internal compression angle, and length. Author

Descriptors:

• *GUIDED MISSILE MODELS
• SHROUD RINGS
• BASE FLOW
• STABILIZATION
• BASE PRESSURE
• SECONDARY FLOW
• FLOW FIELDS
• INTERFERENCE
• DRAG
• JET FLOW

Subject Categories:

• Guided Missile Dynamics, Configurations and Control Surfaces

Distribution Statement:

APPROVED FOR PUBLIC RELEASE