Accession Number:

AD0760039

Title:

Possible Condensation in Rocket Exhaust Plumes 2

Descriptive Note:

Special technical rept.

Corporate Author:

YALE UNIV NEW HAVEN CT DEPT OF ENGINEERING AND APPLIED SCIENCE

Personal Author(s):

• Wu, Benjamin J.

Report Date:

1973-04-01

Pagination or Media Count:

45.0

Abstract:

The results of a computational study of one aspect of condensation in the exhaust plume consisting of H2O and H2 of an Apollo rocket engine are reported. Saturation of water vapor occurs at about 225K in the plume. Hydrogen remains unsaturated in the given flow field. Under the assumption of steady state nucleation, onset of H2O condensation by homogeneous nucleation is estimated to occur at x47, 40, and 13 m, i.e., about 45, 38, and 13 m downstream of the nozzle exit plane, along theta0.0, 0.3, and 0.8 stream tubes, respectively. It is further estimated that at x150 m along the center stream tube a cloud of ten billion H2O dropletscm3 is formed. The mass mean radius of this cloud of droplets is about 17 angstrom, and there are only about 1100 as many droplets with r14 angstrom or 21 angstrom as with r17 angstrom.

Descriptors:

• *EXHAUST GASES
• *ROCKET ENGINES
• FLOW FIELDS
• LIQUID PROPELLANT ROCKET ENGINES
• SPECIFIC HEAT
• WATER VAPOR
• CONDENSATION
• NUCLEATION
• REACTION KINETICS
• NUMERICAL METHODS AND PROCEDURES

Subject Categories:

• Combustion and Ignition
• Liquid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE