AN INVESTIGATION OF THE OXIDIZER FLOW PASSAGES IN A DUAL-COMBUSTION LIQUID ROCKET ENGINE.

Abstract

This work was undertaken to determine the pressure drops in the oxidizer flow passages of a compact dual-combustion liquid rocket engine by means of fluid dynamic model tests, using air instead of liquids, to establish design data. Investigated also were flow distributions and flow instabilities by measurements and flow visualization methods. Changes are indicated to improve the original design. The air tests were carried out over a range of Reynolds numbers to establish the effect of compressibility on the pressure drop loss coefficients. Water tests were undertaken to check the validity of the results and of the proposed calculating method. (Author)

Document Details

• Document Type: Technical Report
• Publication Date: Sep 01, 1967
• Accession Number: AD0840315

Entities

People

• Robert Joseph Kelly

Organizations

• Naval Postgraduate School

Tags

Communities of Interest

• Weapons Technologies

DTIC Thesaurus Topics

• Coefficients
• Combustion
• Compressive Properties
• Engines
• Flow
• Flow Visualization
• Instability
• Measurement
• Model Tests
• Reynolds Number
• Rocket Engines
• Rockets
• Visualizations

Fields of Study

• Engineering

Readers

• Combustion and Flow Dynamics.
• Rocket Propulsion.