Thermal Ionization of Rocket Exhaust Plumes
Abstract
Thermal or equilibrium processes contribute to the total ionization of the exhaust plasmas attending a missile in flight. Such equilibrium ionization is the principal contributor to the total ionization in some cases of interest. Calculations of the equilibrium values of ionization for various rocket-propellant components are presented in graphical form to make numeric values readily available and to simplify their utilization.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 30, 1962
- Accession Number
- AD0282941
Entities
People
- B. N. Navid
- W. W. Balwanz
Organizations
- United States Naval Research Laboratory