VELOCITY MEASUREMENTS IN THE UNIVERSITY OF SOUTHAMPTON HYPERSONIC GUN TUNNEL

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Abstract:

A method of measuring flow velocity by ob erving the propagation of a cylindrical shock wave produced by a long 1. in. PARK DISC RGE IS D SCRIBED. Results are given of measurements made in air at a Mach number of approximately eleven using the University of Southampton hypersonic gun tunnel. Stagnation temperatures, over a range of initial conditions, ere c lculated from the velocity result , an llow nce being made for the caloric i perf ction of the air. A m ximum possible error of plus or minus 4 in the stagna ion temper ture 800 to 1,400 K is claimed. During a run of 40 m sec, considerable cooling of the air in the stagnation region was observed up to 30 loss in stagnation temperature causing a variation in flow properties with time. The possibility of using thi method to me sure the density of the flow is discussed briefly. A UTHOR

Author(s):
Merritt, G. E.
Author Organization(s):
SOUTHAMPTON UNIV (ENGLAND)
Pagination:
0001

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
ARL-144
Contract/Grant Number(s):
AF61 052 250
Monitor Series:
144
 Subject Terms
Joint Capability Areas:
JCA_3.2_Engagement; JCA_3_Force Application
Communities of Interest:
No COI(s) Identified
Descriptor(s):
*HYPERSONIC FLOW, BOUNDARY LAYER, CHRONOMETERS, GAS DISCHARGES, HYPERSONIC WIND TUNNELS, HYPERVELOCITY GUNS, INSTRUMENTATION, MEASUREMENT, OSCILLOSCOPES, PHOTOGRAPHIC ANALYSIS, PHOTOMULTIPLIER TUBES, SCHLIEREN PHOTOGRAPHY, VELOCITY
Report Date:
1961 Apr 01