Results 31 to 40 of about 678 (224)

Numerical Simulation of Reactive Flows in Overexpanded Supersonic Nozzle with Film Cooling

International Journal of Aerospace Engineering, 2015
Reignition phenomena occurring in a supersonic nozzle flow may present a crucial safety issue for rocket propulsion systems. These phenomena concern mainly rocket engines which use H2 gas (GH2) in the film cooling device, particularly when the nozzle ...
Mohamed Sellam, Amer Chpoun
doaj   +1 more source

Hybrid Rocket Engine Noise: Measurements and Predictions of Acoustic Environments from Horizontal Static Fire

Applied Sciences, 2023
A rocket’s turbulent jet radiates intense acoustic waves, which are an acoustic load for structural components like payload, launch structure, and rocket avionics, and impact communities near the launch site.
Giovanni Fasulo, Luigi Federico, Adolfo Sollazzo, Luciano De Vivo, Roberto Citarella   +4 more
doaj   +1 more source

A Simplified Thermal Analysis Model for Regeneratively Cooled Rocket Engine Thrust Chambers and Its Calibration with Experimental Data

Aerospace, 2023
An essential part of the design of a liquid rocket engine is the thermal analysis of the thrust chamber, which is a component whose operative life is limited by the maximum allowable wall temperature and heat flux.
Matteo Fagherazzi, Marco Santi, Francesco Barato, Marco Pizzarelli   +3 more
doaj   +1 more source

Comparative results of computational and theoretical study of the annular nozzle with a flat central body

Вестник Самарского университета: Аэрокосмическая техника, технологии и машиностроение
One of the ways to improve specific characteristics of the power plant of a launch vehicle for ladeploying payload to the near-Earth space is to provide the possibility of operation of a fixed nozzle in the design mode over the whole active leg of the ...
A. A. Kirshina, A. A. Levikhin, A. Yu. Kirshin   +2 more
doaj   +1 more source

New Contour Design Method for Rocket Nozzle of Large Area Ratio

International Journal of Aerospace Engineering, 2019
A rocket engine for space propulsion usually has a nozzle of a large exit area ratio. The nozzle efficiency is greatly affected by the nozzle contour.
Dechuan Sun, Tianyou Luo, Qiang Feng
doaj   +1 more source

A Coupled Heat Transfer Calculation Strategy for Composite Cooling Liquid Rocket Engine

Aerospace, 2023
To better understand the characteristics of coupled heat transfer in liquid rocket engines, a calculation scheme is proposed in this paper. This scheme can simulate the coupled heat transfer processes, including combustion and flow in the thrust chamber,
Bo Xu, Bing Chen, Jian Peng, Wenyuan Zhou, Xu Xu   +4 more
doaj   +1 more source

Supersonic Flow Separation with Application to Rocket Engine Nozzles

Applied Mechanics Reviews, 2005
The past decade has seen a qualitative advancement of our understanding of physical phenomena involved in flow separation in supersonic nozzles; in particular, the problem of side loads due to asymmetrical pressure loads, which constitutes a major restraint in the design of nozzles for satellite launchers.
J. O¨stlund, B. Muhammad-Klingmann
openaire   +2 more sources

Simulation and Application of a New Multiphase Flow Ablation Test System for Thermal Protection Materials Based on Liquid Rocket Engine

Aerospace, 2022
Internal flow field ablation is an important issue in thermal protection materials for rocket engines and hypersonic vehicles. In this paper, a new multiphase flow ablation test system, with an Al2O3 particle delivery device based on an oxygen-kerosene ...
Qingdong Su, Bailin Zha, Jinjin Wang, Mingxia Yan, Yong Gao, Zhensheng Sun, Weifeng Huang   +6 more
doaj   +1 more source

The Future of Hydrogen‐Powered Aviation: Technologies, Challenges, and a Strategic Roadmap for Sustainable Decarbonization

Advanced Energy and Sustainability Research, EarlyView.
Hydrogen‐powered aviation offers a transformative pathway to zero‐emission flight by eliminating in‐flight CO2 emissions. Key considerations include propulsion systems (fuel cells and hydrogen combustion), cryogenic storage and insulation challenges, infrastructure and cost barriers, and supply‐chain constraints.
Mubasshira, Md Mahbubur Rahman, Karib Hassan Khan, Md Nizam Uddin, Dewan Hafiz Nabil   +4 more
wiley   +1 more source

Shock Wave and Aeroelastic Coupling in Overexpanded Nozzle

Aerospace
The growing demand for increasing the engine power of a liquid rocket is driving the development of high-power De-Laval nozzles, which is primarily achieved by increasing the expansion ratio.
Haifeng Hu, Xinni Gao, Yushan Gao, Jianwen Yang   +3 more
doaj   +1 more source