Accession Number:

AD0601616

Title:

AN APPROXIMATE METHOD FOR CALCULATING THE FLOW FIELD OF A ROCKET EXHAUSTING INTO A VACUUM

Descriptive Note:

Engineering Analysis Technical note no. 24

Corporate Author:

PHILCO RESEARCH LABS NEWPORT BEACH CA

Personal Author(s):

• Karydas, A. I.
• Kato, H. T.

Report Date:

1964-06-15

Pagination or Media Count:

30.0

Abstract:

An approximate method for determining the far field flow properties of a rocket exhausting into a vacuum is presented. The technique described is based on radial flow and assumes a density variation both along and normal to the jet centerline. The resulting jet flow field is compared with solutions by the method of characteristics and is shown to have good agreement. Example calculations are provided to demonstrate the present method.

Descriptors:

• *EXHAUST GASES
• *GAS FLOW
• *ROCKET NOZZLES
• FLUID FLOW
• INTEGRAL EQUATIONS
• MATHEMATICAL ANALYSIS
• VACUUM

Subject Categories:

• Rockets
• Combustion and Ignition

Distribution Statement:

APPROVED FOR PUBLIC RELEASE