Amanote Research
Register
Sign In
Flow Separation in Rocket Nozzles Under High Altitude Condition
Shock Waves
- United States
doi 10.1007/s00193-016-0631-6
Full Text
Open PDF
Abstract
Available in
full text
Categories
Astronomy
Physics
Mechanical Engineering
Date
March 18, 2016
Authors
R. Stark
C. Génin
Publisher
Springer Science and Business Media LLC
Related search
Perturbation Analysis of One-Dimensional Heterogeneous Flow in Rocket Nozzles
Numerical Prediction of Compressible Heat Flow With Complex Wall Temperature in Supersonic Rocket Nozzles
Thermal Science
Renewable Energy
the Environment
Sustainability
Numerical Simulation of Radiation in High Altitude Solid Propellant Rocket Plumes
Acta Astronautica
Aerospace Engineering
Analysis on Flow Separation Characteristics of Last Stage Blade in Steam Turbine Under Small Volume Flow Condition
Thermal Science
Renewable Energy
the Environment
Sustainability
Numerical Studies on Thrust Augmentation in High Area Ratio Rocket Nozzles by Secondary Injection
Journal of Applied Fluid Mechanics
Mechanics of Materials
Condensed Matter Physics
Mechanical Engineering
Application of a Multiscale Particle Scheme to High Altitude Rocket Exhaust Flows
Numerical Simulation of Shock-Induced Separated Flows in Overexpanded Rocket Nozzles
Coolant Pressure Losses in Regenerative Cooled Liquid Rocket Chambers and Nozzles
Houille Blanche
Water Science
Technology
Analysis of Wind Tunnel Test Results of Fluidic Generator for High-Altitude Rocket
