TASK R

Abstract

High temperature kinetics in laminar flames; Work continued on checking the reliability of the scavenger probe sampling technique for measuring O-atom concentration. Comparisons were made between this method and the NO2 titration method. Thermal conductivity of gases; Improvements in the mixing and vaporizing accessories to the line source apparatus have helped to alleviate the flow fluctuations previously noted in the H2O-O2 study. Data are given for results on pure O2 and on a mixture of 25 mole % H2O - 75 mole % O2 over the temperature range 400 - 1100 K. Rocket nozzle fluid dynamics; Boundary layer measurement at the 2-in. station downstream of the throat were initiated. Results on four tests of throat heat transfer rates are given and compared with theory. Infrared absorption results on CO2 and CO in the 12.5 degree nozzle are presented. Rocket nozzle chemical kinetics; A new series of calculations of non-equilibrium flow through a supersonic expansion section has been undertaken for H2-air combustion products. (Author)

Document Details

Document Type
Technical Report
Publication Date
Mar 31, 1962
Accession Number
AD0275325

Entities

Organizations

  • Johns Hopkins University

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Chemical Kinetics
  • Combustion Products
  • Dynamics
  • Fluid Dynamics
  • Gas Turbine Nozzles
  • Heat Transfer
  • High Temperature
  • Kinetics
  • Nozzles
  • Rocket Nozzles
  • Thermal Conductivity

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Combustion science or combustion engineering.
  • Software Engineering

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight
  • Hypersonics - Hypersonic Flow