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

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)

Document Details

Document Type
Technical Report
Publication Date
Oct 16, 1957
Accession Number
AD0831282

Entities

People

  • G. C. Wilson

Organizations

  • General Dynamics

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Heating
  • Boundary Layer
  • Computer Programs
  • Computers
  • Digital Computers
  • Fuel Tanks
  • Heat Energy
  • Heat Exchangers
  • Heat Transfer
  • Liquid Oxygen
  • Propellant Tanks
  • Turbulent Boundary Layer

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Computer Science.
  • Rocket Propulsion.