ROCKET PLUME RADIANCE. V. CALCULATION OF ADIABATIC FLAME TEMPERATURES OF AFTERBURNING ROCKET EXHAUST,
Abstract
Thermochemical calculations have been applied to the afterburning of oxygen-hydrocarbon rocket plumes with arbitrary amounts of entrained air. The composition and temperature at the nozzle exit are found by considering the expansion to take place in two distinct stages. During the first stage, the gases are in chemical equilibrium; during the second, the composition is constant. The transition point is determined by matching experimental and calculated performance curves. The exit gases are expanded to ambient pressure and mixed with various arbitrary amounts of air. Momentum and energy are conserved during the mixing. The mixed gases are then allowed to react to equilibrium to determine the adiabatic flame temperature. Temperatures of the mixed gases are reported with and without reaction for a hypothetical missile trajectory. It is found that afterburning can raise the temperature of the plume by as much as 1000K. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 16, 1960
- Accession Number
- AD0686976
Entities
People
- Frederick P. Boynton
- John T. Neu
Organizations
- General Dynamics