STUDY OF FORCES ON PROPELLANTS DUE TO HEAT TRANSFER INFLUENCING PROPELLANT TEMPERATURE IN A RECOVERY-TYPE VEHICLE.
Abstract
The heat transfer problem in a partially filled propellant tank system of an Agena space vehicle was formulated in a lumped capacity form which can be solved in principle by using an analog computer. The heat transfer mechanisms considered contain internal radiation, phase change due to evaporation and condensation, conduction, free convection and convection in liquid layers due to differential surface tension. Transport properties for gaseous UDMH, IRFNA and mixtures of helium with each gas were obtained by computation and experiment. Mass diffusivities for two and three component mixtures were computed by the methods of Bird, Stewart and Lightfoot. Viscosities and heat capacities for gaseous HDMH and nitric acid were rigorously computed; thermal conductivities of single gases were then calculated from the Eucken equation. Thermal conductivities of gas mixtures were calculated from the Mason-Saxena equations. Computed thermal conductivities were compared with experimental values obtained by means of a modified hot wire method employing five standard gases of various molecular weights. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 15, 1963
- Accession Number
- AD0615618