Accession Number:

AD0829820

Title:

A PRELIMINARY ANALYSIS OF ROCKET EXHAUST JET EFFECTS ON MISSILE SKIN AND BASE PRESSURES AT MACH 0.6 AND 1.5 - NACA LEWIS FLIGHT PROPULSION LABORATORY TEST 2093,

Descriptive Note:

Corporate Author:

GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA

Personal Author(s):

• Powell, G. E.

Report Date:

1958-08-19

Pagination or Media Count:

16.0

Abstract:

A wind tunnel test of a one-thirtieth scale B series Atlas missile with operating rocket engines was run at the NACA Lewis 8-by-6 foot supersonic wind tunnel. The primary test objective was to determine the amount of rocket and gas turbine exhaust recirculation into the missile base region a secondary objective was to determine the effect of operating rockets on missile skin and base pressure. Only the pressure data are considered in this report. Author

Descriptors:

• *LIQUID PROPELLANT ROCKET ENGINES
• CAPTIVE TESTS
• SURFACE TO SURFACE MISSILES
• MODEL TESTS
• WIND TUNNEL MODELS
• SUPERSONIC CHARACTERISTICS
• SECONDARY FLOW
• BASE PRESSURE
• AIRFRAMES
• GAS TURBINES
• EXHAUST GASES
• BASE FLOW
• FORCE(MECHANICS)
• SCALE
• ROCKET NOZZLES
• THERMAL RADIATION
• TURBOJET EXHAUST NOZZLES
• SUSTAINER ENGINES
• BOOSTER ROCKET ENGINES

Subject Categories:

• Guided Missile Dynamics, Configurations and Control Surfaces
• Liquid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE