Add to ORKGSmall liquid rocket engine (SLRE) with calorimeter were developed and tested to evaluate cooling characteristics in the liquid rocket engine. Therefore, cooling performance analysis was performed to predict the heat transfer coefficient on gas side wall in 10 calorimeter channel. A heat transfer empirical formula was determined by results of firing test and computational simulation.This paper is the part of research results which is performed in NRL Project, "The development of liquid rocket engine with regenerative cooling system". We appreciate the related person who supports this project
Rocket engines are highly complex and technical propulsion devices that are used to position objects...
Includes bibliographical references (pages 38-41)An analytical method was developed to predict the t...
The increasing specific impulse of the liquid rocket engine (LRE), which is designed to operate in s...
Small liquid rocket engine (SLRE) with calorimeter were developed and tested to evaluate cooling ch...
Film cooling in combination with regenerative cooling is presently considered as an efficient method...
High combustion temperatures and long operation durations require the use of cooling techniques in l...
Most large scale rocket engines use a regeneratively cooled system to cool the rocket engine using e...
Most large scale rocket engines use a regeneratively cooled system to cool the rocket engine using e...
A computational procedure able to describe the coupled hot-gas/wall/coolant environment that occurs ...
International audienceFlow evolution and heat transfer capability in the cooling system of liquid ro...
High combustion temperatures and long operation durations require the use of cooling techniques in l...
Combustion within rocket engines produces a harsh environment, where chambers experience conditions ...
Heat transport processes have been an ongoing interest at the DLR Institute of Space Propulsion. The...
The NASA MIRO Center for Space Exploration and Technology Research (cSETR) located at the University...
The NASA MIRO Center for Space Exploration and Technology Research (cSETR) located at the University...
Rocket engines are highly complex and technical propulsion devices that are used to position objects...
Includes bibliographical references (pages 38-41)An analytical method was developed to predict the t...
The increasing specific impulse of the liquid rocket engine (LRE), which is designed to operate in s...
Small liquid rocket engine (SLRE) with calorimeter were developed and tested to evaluate cooling ch...
Film cooling in combination with regenerative cooling is presently considered as an efficient method...
High combustion temperatures and long operation durations require the use of cooling techniques in l...
Most large scale rocket engines use a regeneratively cooled system to cool the rocket engine using e...
Most large scale rocket engines use a regeneratively cooled system to cool the rocket engine using e...
A computational procedure able to describe the coupled hot-gas/wall/coolant environment that occurs ...
International audienceFlow evolution and heat transfer capability in the cooling system of liquid ro...
High combustion temperatures and long operation durations require the use of cooling techniques in l...
Combustion within rocket engines produces a harsh environment, where chambers experience conditions ...
Heat transport processes have been an ongoing interest at the DLR Institute of Space Propulsion. The...
The NASA MIRO Center for Space Exploration and Technology Research (cSETR) located at the University...
The NASA MIRO Center for Space Exploration and Technology Research (cSETR) located at the University...
Rocket engines are highly complex and technical propulsion devices that are used to position objects...
Includes bibliographical references (pages 38-41)An analytical method was developed to predict the t...
The increasing specific impulse of the liquid rocket engine (LRE), which is designed to operate in s...