Accession Number:

AD0491391

Title:

AIR FLOW ABOUT CONE CYLINDERS WITH CURVED SHOCK WAVES,

Descriptive Note:

Corporate Author:

ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD

Personal Author(s):

Report Date:

1952-09-01

Pagination or Media Count:

33.0

Abstract:

Flows about 35 degrees cone cylinders in free flight at Mach numbers ranging from the regime of detached shocks to the region where completely supersonic Taylor-Maccoll flow has been established have been investigated with interferometric techniques. Measured fringe shifts from the interferograms, density distributions, and the corresponding pressures have been compared with theorectical predictions and wind tunnel data. Good agreement has been found with theory and other experiments. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE