Accession Number:

AD0255718

Title:

EXPERIMENTAL INVESTIGATION OF STAGE SEPARATION AERODYNAMICS

Descriptive Note:

Technical note

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC

Personal Author(s):

Report Date:

1961-05-01

Pagination or Media Count:

27.0

Abstract:

Interstage aerodynamic pressure that occurs during stage separation was investigated for a two-stage missile at a Mach number of 2.0 and an altitude of 38,000 feet in the NASA Lewis 8- by 6-foot supersonic wind tunnel. The model consisted of a wing-supported second stage having a cold-air simulated rocket motor operated at a constant total pressure, and a sting-supported, translating first stage. Separation distance was varied up to 3 second-stage body diameters. Effects of stage misalignment were studied by displacement of stage centerlines over a range up to 1 second-stage diameter. First- to second-stage diameter ratios were1.0, 1.25, and 1.5. First-stage interference effects produced higher-than-ambient second-stage base pressures over a longer separation distance for jet-off staging than for jet-on. First-stage ports for rocket-on staging reduced the distance of first-stage interference effects. Ports also reduced but did not eliminate fluctuating second-stage base and afterbody pressures that occurred at separation distances less than 1 diameter for rocket-on staging.

Subject Categories:

  • Manufacturing and Industrial Engineering and Control of Production Systems
  • Guided Missiles
  • Fluid Mechanics
  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE