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Accession Number:

AD1175627

Title:

Effects of Cone Tip Changes on Wall-Cooled Hypersonic Boundary Layer Transition and Turbulence

Author(s):

• Major, Mathew M.

Author Organization(s):

• AIR FORCE INSTITUTE OF TECHNOLOGY WRIGHT-PATTERSON AFB OH

Report Date:

2022-03-24

Abstract:

Boundary layer measurements took place at Air Force Research Labs (AFRL) Mach-6 Ludwieg tube hypersonic wind tunnel on a 7-degree half angle spherically blunted nose cone with a 1.5 mm radius to study the effects of a cooled surface on the transition process. Experiments compared uncooled and cooled flow conditions on the blunt-nosed model, and then compared to past data for a sharp-tipped cone of similar geometry. Cooling the surface delayed the onset of transition on the blunt nose model. Combining the effects of nose blunting and cooling further increased transition delay than each acting individually compared to the sharp-tipped case. This outcome provides much needed data in an area of study with inconclusive results.

Document Type:

Conference:

Journal:

Pages:

162

File Size:

15.98MB

Contracts:

Grants:

Descriptors:

• fluid dynamics
• boundary layer
• computational fluid dynamics
• fluid mechanics
• fluid flow
• turbulent flow
• geometry
• air force
• military research
• test facilities
• wind tunnels
• boundary layer control
• boundary layer flow
• change detection
• mechanics
• physics laboratories
• surface properties

Identifiers:

• Hypersonic
• Boundary Layer Transition
• Nose Bluntness
• Surface Temperature

SubjectCategory:

• Physics
• Test Equipment, Research Facilities and Reprography

Communities of Interest:

• Space

Distribution Statement:

Approved For Public Release

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