Accession Number:

AD0632714

Title:

LAMINAR AND TURBULENT BOUNDARY LAYERS ON SLIGHTLY-BLUNTED CONES AT HYPERSONIC SPEEDS

Descriptive Note:

Corporate Author:

NAVAL ORDNANCE LAB WHITE OAK MD

Personal Author(s):

Report Date:

1966-03-21

Pagination or Media Count:

25.0

Abstract:

A momentum-integral method for calculating the boundary-layer growth on slightly-blunted cones has been given in a previous paper by the writer. The method, which was applied to cones with fully laminar flow, is extended in the present paper to turbulent flow. In addition 1 transition data on cones at hypersonic speeds are examined to show the great effect of slight nose blunting on interpretation of the results, 2 agreement between measured and calculated cone drag coefficients for fully laminar flow is demonstrated, and 3 turbulent friction and boundary-layer thickness calculations are shown to agree with the limited amount of ballistics range data which are available.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE