Accession Number:

AD0606563

Title:

SIMILITUDE IN THE TTESTING OF SOLID PROPELLANT ROCKET NOZZLES,

Descriptive Note:

Corporate Author:

ARMY MATERIALS RESEARCH AGENCY WATERTOWN MASS

Personal Author(s):

Report Date:

1964-07-01

Pagination or Media Count:

72.0

Abstract:

The fluid flow, heat transfer, and stress conditions in a hollow cylinder were analyzed, assuming that the results could be at least qualitatively applied to the actual conditions that exist in and near the throat of a solid propellant rocket nozzle. The possibility of a transition in the hydrodynamic boundary layer flow from laminar to turbulent was included, and the change in results due to such transitions was demonstrated. Two types of nozzle were considered 1 a geometrically similar series with a constant ratio of outside to inside radius, and 2 a series with a constant nozzle exit plane wall thickness. Various results such as working stresss, temperature drop, heat transfer coefficients, etc., are presented for each series both separately and in comparison. The results allow one to determine how various phenomena vary with combustion pressure and throat diameter or Reynolds number, and to plan experiments in which certain phenomena can be held constant. One can compare severity of conditions between model and prototype if small scale tests are planned and determine proper test condnoonditions to accurately simulate prototype conditions. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE