Effect of regenerative cooling on rocket engine specific impulse

Control of LNG Pyrolysis and Application to Regenerative Cooling Rocket Engine

Specific Impulse and Ignition Delay Time Assessment for DMAZ with Liquid Oxidizers for an Upper Stage Rocket Engine

2-Dimethyl amino ethyl azide (DMAZ) has attracted much attention as a suitable liquid fuel replacement for monomethyl hydrazine (MMH) and unsymmetrical dimethyl hydrazine (UDMH) in propellant systems because, in contrast to these fuels, it is noncarcinogen. In this research, performance, and ignition delay time of DMAZ were studied with common liquid oxidizers such as inhibited red fuming n...

Effect of Aspect Ratio on Supercritical Heat Transfer of Cryogenic Methane in Rocket Engine Cooling Channels

The supercritical turbulent flow of cryogenic methane flowing in a rocket engine cooing channel is numerically analysed by imposing constant heat flux at the bottom surface of the channel. The calculation scheme is validated by comparing the results obtained with experimental results reported in literature. The heat transfer coefficient is influenced by the strong variation in thermophysical pr...

ASSESSING THE EFFECT OF BLOCKAGE OF DIRT ON ENGINE RADIATOR IN THE ENGINE COOLING SYSTEM

This thesis looked at the effect of clay and silt soil blocking the heat transfer area of the radiator and its effect on the engine coolant through the conduct of experiments and a mathematical model developed. The results indicated that the percentage area covered resulted in a proportional increase of the inlet and outlet temperatures of the coolant in the radiator. The mathematically mode...

The Blacklight Rocket Engine

Executive Summary This report summarizes the final project results for the period of May 1, 2002 through November 30, 2002 for the NIAC CP 01-02 Phase I study, "The BlackLight Rocket Engine". The objective of the Phase I study was to assess the potential of low pressure, mixed gas hydrogen plasmas (i.e. the BlackLight Process) toward the development of high performance space propulsion systems.