Accession Number:

AD0601379

Title:

THE NUMBERICAL CALCULATION OF THE FLOW FIELD AROUND A REENTRY BODY

Descriptive Note:

Corporate Author:

GENERAL APPLIED SCIENCE LABS INC WESTBURY NY

Personal Author(s):

Report Date:

1962-09-18

Pagination or Media Count:

50.0

Abstract:

The flow field around the Trailblazer I body a sphere with a short cylindrical afterbody was calculated for three flight conditions - 18,900 feet per second at 150,000 feet, 20,200 ft. per second at 200,000 feet, and 20,400 feet per second at 250,000 feet. The method of calculation is to guess a shock shape in the nose region and then to develop the flow field in the slightly supersonic region by the characteristic method. These data serve as input data for a calculation of the purely subsonic region. The result of this second calculation is a body shape which may be compared with the true shape and, if necessary, the assumed shock shape changed. The calculation in the purely supersonic region then proceeds to generate the flow field and shock shape downstream of the nose. These calculations have been programmed for the IBM 704.

Subject Categories:

  • Fluidics and Fluerics
  • Guided Missile Reentry Vehicles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE