Accession Number:

AD0276912

Title:

AERODYNAMIC DESIGN OF A CONTINUOUS HYPERVELOCITY WIND TUNNEL

Descriptive Note:

Corporate Author:

NAVAL ORDNANCE LAB WHITE OAK MD

Personal Author(s):

Report Date:

1962-04-01

Pagination or Media Count:

45.0

Abstract:

A N AERO YNA IC DESIGN STUDY WAS MADE OF A CONTINUOUS, HYPERVELOCI Y IND TU NEL FOR SIMUL I G T E FLIGHT ENVIRONMENT OF LONG-RANGE BALLISTIC MISSILES ND GLIDE V ICLES AT Mach numbers up to 20. Nozzles were designed by the m tho of characteristics for high-temperature air in dissociative and vibrational equilibrium. Since non-equilibriu flow was e pected to occur under many conditions, the effect of a fi ite O r co binatio r te on the flow in hyper onic nozzles was determine for a wide rang of supply conditions. The nozzle turbulent boundary-layer growth and heat ransfer were calculated by a mome tum-integral method e ployi g thermody amic and ransport properties appropriate to hig -temper ure air. The extremely high he t-transf r r tes near the nozzle throat create a severe cooling problem B OTH CONVECTIVE COOLING, USING WATER OR LIQUID METALS, AND FILM COOLING, WITH AIR OR WATER I J CTION RE STUDIED. The application of the electric arc as an air ea ing devic , nd the performance of a hypersonic diffuser were also examined Conclusions re drawn from the resul s of this s udy regarding the range of free-flig t condi io s which can be simul d in the wind unnel.

Subject Categories:

  • Test Facilities, Equipment and Methods

Distribution Statement:

APPROVED FOR PUBLIC RELEASE