Add to ORKGHeat transfer in the converging section of the nozzle of a simulated solid propellant rocket with a star-shaped conduit has been investigated in the following way: (a) Area-average heat transfer has been measured on a room temperature rig, with and without a simulated charge. (b) Theoretical heat transfer has been calculated without the charge (axisymmetric laminar flow). (0) An attempt has been made to predict the detailed distribution of heat transfer by measurements of mass transfer on a nozzle made of napthalene. (d) Flow visualisation has been performed on a water-rig … [cont.]
This paper presents the simulation and experimental results of the dependency of the surface tempera...
A combination of conjugate heat transfer calculations and experiments in a dedicated test rig at Roy...
Experiments were conducted with 1000-pound-thrust rocket engine to determine feasibility of cooling ...
An investigation has been made into the feasibility of predicting mean convective heat transfer coe...
The increasing specific impulse of the liquid rocket engine (LRE), which is designed to operate in s...
Comparison of solid propellant nozzle heat transfer coefficients with predicted dat
Includes bibliographical references (pages 38-41)An analytical method was developed to predict the t...
A 1030:1 carbon steel, heat-sink nozzle was tested. The test conditions included a nominal chamber p...
Comparison of experimental heat transfer coefficients in a nozzle with analytical predictions for va...
The object of the investigations is the nozzles of the solid propellant rocket engine. Experimental ...
About 500 experimental heat transfer data taken from the open literature and relevant to the most th...
One of the objectives of the Solid Propulsion Integrity Program (SPIP) at Marshall Space Flight Cent...
The relative weight of convective and radiative wall heat transfer in liquid rocket engine thrust ch...
The prediction of wall heat flux at the nozzle throat is of paramount importance in liquid rocket en...
Energy thickness in prediction of throat heat transfer in rocket nozzles using nozzle geometries and...
This paper presents the simulation and experimental results of the dependency of the surface tempera...
A combination of conjugate heat transfer calculations and experiments in a dedicated test rig at Roy...
Experiments were conducted with 1000-pound-thrust rocket engine to determine feasibility of cooling ...
An investigation has been made into the feasibility of predicting mean convective heat transfer coe...
The increasing specific impulse of the liquid rocket engine (LRE), which is designed to operate in s...
Comparison of solid propellant nozzle heat transfer coefficients with predicted dat
Includes bibliographical references (pages 38-41)An analytical method was developed to predict the t...
A 1030:1 carbon steel, heat-sink nozzle was tested. The test conditions included a nominal chamber p...
Comparison of experimental heat transfer coefficients in a nozzle with analytical predictions for va...
The object of the investigations is the nozzles of the solid propellant rocket engine. Experimental ...
About 500 experimental heat transfer data taken from the open literature and relevant to the most th...
One of the objectives of the Solid Propulsion Integrity Program (SPIP) at Marshall Space Flight Cent...
The relative weight of convective and radiative wall heat transfer in liquid rocket engine thrust ch...
The prediction of wall heat flux at the nozzle throat is of paramount importance in liquid rocket en...
Energy thickness in prediction of throat heat transfer in rocket nozzles using nozzle geometries and...
This paper presents the simulation and experimental results of the dependency of the surface tempera...
A combination of conjugate heat transfer calculations and experiments in a dedicated test rig at Roy...
Experiments were conducted with 1000-pound-thrust rocket engine to determine feasibility of cooling ...