Accession Number : AD0831282

Title :   OPERATIONAL MISSILE LIQUID OXYGEN AND FUEL TANK SKIN TEMPERATURES DUE TO AERODYNAMIC HEATING AND HELIUM WEIGHT REQUIREMENTS DURING POWERED FLIGHT,

Corporate Author : GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA

Personal Author(s) : Wilson, G. C.

Report Date : 16 OCT 1957

Pagination or Media Count : 27

Abstract : Skin temperatures due to aerodynamic heating on the liquid oxygen and fuel tanks of the operational missile were calculated based on a turbulent boundary layer. Helium weight requirements for the propellant tanks during powered flight were determined for the condition of turbulent free convective heat transfer from the walls to the pressurizing gas, and utilizing fixed-orifice, by-pass heat exchanger data (Reference 6). A pressure of 26 psig was required in the liquid oxygen tank during both booster and sustainer stages in order to satisfy pump inlet and structural requirements. The fuel tank required 60 psig during the booster stage to satisfy structural requirements, but the gas was allowed to expand polytropically during the sustainer stage since the residual pressure was sufficient to satisfy both pump inlet and structural requirements. Results contained in this report are from the IBM 704 digital computer program which has been code-checked against hand-calculated values. (Author)

Descriptors :   *SURFACE TEMPERATURE), (*SURFACE TO SURFACE MISSILES, FLIGHT TESTING), (*PROPELLANT TANKS, AERODYNAMIC HEATING, AERODYNAMIC LOADING, TENSILE PROPERTIES, CAVITATION, PUMPS, STRUCTURAL PROPERTIES, STAGING, TURBULENT BOUNDARY LAYER, DIGITAL COMPUTERS, GUIDED MISSILE TRAJECTORIES, HEAT TRANSFER, WEIGHT, PRESSURIZATION, LIQUID ROCKET OXIDIZERS.

Subject Categories : Surface-launched Guided Missiles
      Thermodynamics
      Liquid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE