An experimental study of static pressure probe geometries and probe mounts in hypersonic flow.

摘要

Static pressure probe geometries and probe mounts that would generate the least interference and give the best response, to be later used in flow reconstruction in ducts or inlets in hypersonic flow of Mach 8.36, were investigated as part of research toward air breathing engine development. Biconical and conventional cone/cylinder type static pressure probes were tested. The response of a probe on a cylindrical mount, which was required to allow insertion of probe into the duct, was compared to one on a wedge. A shock generator was used to observe the effects of the presence or absence of a probe near the flat plate. It was concluded that a cone/cylinder type probe installed on a wedge mount of at most 35{dollar}spcirc{dollar} included angle is the most suitable and would not interfere with wall pressure readings whereas the cylindrical mount causes great interference and hence is unstable.