NUMERICAL SIMULATION OF UNSTEADY AND NONLINEAR INTRACHAMBER PROCESSES WHEN TRIGGERING ROCKET ENGINE ON SOLID FUEL FOR SPECIAL PURPOSE. PART 1. STATEMENT OF COMPUTATIONAL EXPERIMENT

2016 ◽  
pp. 53-72
Author(s):  
Mikhail Egorov ◽  
◽  
Sergey Egorov ◽  
Dmitry Egorov ◽  
Roman Mormul ◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Solid Fuel ◽  
Computational Experiment ◽  
Rocket Engine

Decoupled numerical simulation of a solid fuel fired retort boiler

2014 ◽  
Vol 73 (1) ◽  
pp. 794-804 ◽  
Author(s):  
Arkadiusz Ryfa ◽  
Rafal Buczynski ◽  
Michal Chabinski ◽  
Andrzej Szlek ◽  
Ryszard A. Bialecki
Keyword(s):  
Numerical Simulation ◽  
Solid Fuel

scholarly journals NUMERICAL INVESTIGATION OF THE EFFECT OF AERODYNAMIC FRAGMENTATION OF CONDENSATE PARTICLES ON THE TWO-PHASE IMPULSE LOSSES IN A SOLID-FUEL ROCKET ENGINE NOZZLE

2017 ◽  
pp. 88-94
Author(s):  
Nikolay Nikolaevich DYACHENKO ◽  
◽  
Lyudmila Ivanovna DYACHENKO ◽  
Valeriya Sergeevna GUROVA ◽  
Sofiya Aleksandrovna SINEOKAYA ◽  
...  
Keyword(s):  
Numerical Investigation ◽  
Solid Fuel ◽  
Rocket Engine ◽  
Two Phase

90% Hydrogen Peroxide/Polyethylene Solid Fuel Hybrid Rocket Engine

2005 ◽  
Author(s):  
Nobuo Tsujikado ◽  
Masatoshi Koshimae ◽  
Rikiya Ishikawa ◽  
Kazuki Kitahara ◽  
Atsushi Ishihara
Keyword(s):  
Hydrogen Peroxide ◽  
Solid Fuel ◽  
Rocket Engine ◽  
Hybrid Rocket ◽  
Hybrid Rocket Engine

Numerical Simulation of Cold Swirl Field for Solid Fuel Ramjet with NACA Airfoil

2014 ◽  
Vol 716-717 ◽  
pp. 711-716
Author(s):  
Jie Yu ◽  
Xiong Chen ◽  
Hong Wen Li
Keyword(s):  
Numerical Simulation ◽  
Flow Field ◽  
Radial Velocity ◽  
Solid Fuel ◽  
Velocity Gradient ◽  
Pressure Loss ◽  
Total Pressure ◽  
Swirl Flow ◽  
Total Pressure Loss ◽  
Swirl Number

In order to study the swirl flow characteristics in the solid fuel ramjet chamber, a new type of annular vane swirler with NACA airfoil is designed. The cold swirl flow field in the chamber is numerically simulated with different camber and t attack angle, while the swirl number , swirl flow field structure, total pressure recovery coefficient were studied. According to numerical simulation result, the main factors in swirl number are camber and angle of attack, the greater angle of attack, the greater the camber ,the stronger swirl will be. Results show that the total pressure loss is mainly concentrated in the inlet section, the total pressure loss cause by vane swirler is small. Radial velocity gradient exists in swirling flow, and increases with the swirl number. With the influence of centrifugal force and combustion chamber structure, the radial velocity gradient increases.

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