Accession Number:

AD0747477

Title:

Design of a High Reynolds Number Mach Number 8 Contoured Nozzle for the Hypervelocity Wind Tunnel (F).

Descriptive Note:

Final rept. Jan-Jun 71,

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AIR FORCE STATION TENN

Personal Author(s):

Report Date:

1972-08-01

Pagination or Media Count:

53.0

Abstract:

The report describes the aerodynamic design of a Mach 8 contoured nozzle for a hypervelocity wind tunnel. The nozzle is expected to operate over a broad range of reservoir conditions including temperatures and pressures which will allow the simulation of flight conditions at 70,000-ft altitude. Both tunnel blockage considerations and tunnel core size estimates indicate that 4.5-in.-diam very blunt 6-in. diam hemisphere models, and larger diameter sharp nose models could be tested. This method may be used to extrapolate boundary-layer predictions to higher Reynolds numbers. Author

Subject Categories:

  • Test Facilities, Equipment and Methods

Distribution Statement:

APPROVED FOR PUBLIC RELEASE