Accession Number:

ADP005919

Title:

Aerodynamic Heating of Missiles,

Descriptive Note:

Corporate Author:

DORNIER G M B H FRIEDRICHSHAFEN (GERMANY F R)

Personal Author(s):

Report Date:

1988-04-01

Pagination or Media Count:

19.0

Abstract:

This paper presents results of investigations of the aerodynamic heating of missiles. First the applied basic semiempirical methods to determine the flow field about the isolated components of missiles are described and some possibilities to calculate the heat flux in the boundary layer are specified for different pointed or blunt body noses, such as conical, ogival and hemispherical noses. The methods are valid for laminar and turbulent flow properties and in the transition region between laminar and turbulent. The calculated heat transfer factors or Stanton numbers are compared with experimental results. Agreement between theoretical and measured values is good. Next, a theoretical method for the calculating flow fields around missile configurations is presented. This method is based on the parabolization of the compressible, stationary Navier-Stokes equations and is limited to supersonic Mach numbers. The quality of the results is demonstrated by comparison to corresponding test results of other authors. Finally a computational method is described to calculate the local time-dependent temperatures at the surface or inside the body. The configuration is divided into a number of volume elements, thus permitting numerical solution of the time varying equation of heat transfer. The resulting temperatures for some special configurations are plotted and, when possible, compared with experimental results.

Subject Categories:

  • Fluid Mechanics
  • Guided Missiles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE