Accession Number:

AD0722346

Title:

NOL Hypervelocity Wind Tunnel Report No. III: Theoretical Analysis of the Boundary Layer in the Nozzle,

Descriptive Note:

Corporate Author:

NAVAL ORDNANCE LAB WHITE OAK MD

Personal Author(s):

Report Date:

1971-02-26

Pagination or Media Count:

44.0

Abstract:

The equations used to calculate the boundary layer properties for use in the design of the Mach 10, 15, and 20 axisymmetric nozzles of the hypervelocity wind tunnel at NOL are derived. One equation is the integral moment-of-momentum differential equation for the boundary layer velocity profile shape parameter the form of the equation is valid for a real gas. This equation is used with an axisymmetric integral momentum equation that is valid for thick as well as for thin boundary layers to calculate the total thickness and the displacement effect of the boundary layer. Author

Subject Categories:

  • Test Facilities, Equipment and Methods
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE