Multimatrix Composite Materials for Rocket Nozzle Manufacturing: A Comparative Review. [PDF]
Polymers (Basel)Meiirbekov M +7 more
europepmc +1 more source
Comparison of theoretical and experimental thrust performance of a 1030:1 area ratio rocket nozzle at a chamber pressure of 2413 kN/m2 (350 psia) [PDF]
The joint Army. Navy, NASA. Air Force (JANNAF) rocket engine peformnace prediction procedure is based on the use of various reference computer programs. One of the reference programs for nozzle analysis is the Two-Dimensional Kinetics (TDK) Program.
Kacynski, Kenneth J. +2 more
core +1 more source
Deployable Rocket Nozzle Utilizing Superelastic Titanium Alloy Sheet
, 2019 Hirobumi Tobe +3 more
openalex +2 more sources
Nano-Iron as a Catalyst in Isocyanate-Free Rocket Propellants. [PDF]
Polymers (Basel)Chmielarek M +2 more
europepmc +1 more source
Experimental evaluation of heat transfer on a 1030:1 area ratio rocket nozzle [PDF]
A 1030:1 carbon steel, heat-sink nozzle was tested. The test conditions included a nominal chamber pressure of 2413 kN/sq m and a mixture ratio range of 2.78 to 5.49. The propellants were gaseous oxygen and gaseous hydrogen.
Kacynski, Kenneth J. +2 more
core +1 more source
NUMERICAL INVESTIGATION OF HOT GAS-INDUCED FLOW SEPARATION IN ROCKET NOZZLES
ROJAS SEGOVIA Fernando Alejandro +4 more
openalex +1 more source
Two-Dimensional Modeling of Ablation and Pyrolysis with Application to Rocket Nozzles [PDF]
, 2016 Peter Cross, Iain D. Boyd
openalex +1 more source
Starting modes of multidirectional electrodeless plasma thruster with closed ring-shaped gas discharge chamber. [PDF]
Sci RepShumeiko AI +4 more
europepmc +1 more source