A Supersonic/Hypersonic Aerodynamic Investigation of the Saturn IB/Apollo Upper Stage

Abstract

The static stability and axial force characteristics of an upper stage Saturn IB/Apollo model were investigated in a series of wind tunnel tests at Mach numbers between 1.93 and 8.05. This report presents and analyzes the results of these small scale studies. Test procedures and models are described, and consideration of boundary layer characteristics and violated modeling rules yields an assessment of the validity of the data Four basic models provided evaluation of the basic launch vehicle characteristics, as well as the effects of two modes of mission abort and jettison of the launch escape system. The launch configuration experienced sudden, strong changes in stability derivatives and axial force coefficients near Mach 5. No similar changes were observed on the other configurations. Effects of Reynolds number, Mach number, and boundary layer trips were obtained for each shape. The faired curves are believed to be valid for full-scale flight of the Saturn IB/Apollo upper stage .

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1966
Accession Number
ADA455599

Entities

People

  • David R Carlson
  • William P. Walters

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Boundary Layer
  • Boundary Layer Trips
  • Coefficients
  • Escape Systems
  • Flow Fields
  • Fluid Dynamics
  • High Altitude
  • Layers
  • Mach Number
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Service Modules
  • Turbulent Mixing
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computational Modeling and Simulation

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow