NASA NTRS · 19660061353
A new technique for simulating rocket engine flow for study of base heating problems.
Abstract
Short duration technique providing simulation of thermodynamic properties and composition of exhaust products of liquid and solid propellant rocket engines
Explore related subjects
Keep this discovery
Explore connections, maps & timelines
Wilson, H. B., Jr.. 1966-09-01. A new technique for simulating rocket engine flow for study of base heating problems.. https://ntrs.nasa.gov/citations/19660061353
Cite the original work for its findings. Save a collection to share your selection of sources.