Accession Number:

AD0092632

Title:

A STUDY OF THE END WALL BOUNDARY LAYER IN AN AXIAL COMPRESSOR BLADE ROW

Descriptive Note:

Corporate Author:

MASSACHUSETTS INST OF TECH CAMBRIDGE GAS TURBINE LAB

Personal Author(s):

• Moore, Jr., Raymond W.
• Richardson, David L.

Report Date:

1955-10-01

Pagination or Media Count:

62.0

Abstract:

Descriptors:

• *TURBULENT BOUNDARY LAYER
• *AXIAL FLOW COMPRESSOR BLADES
• MATHEMATICAL ANALYSIS
• VELOCITY

Subject Categories:

• Hydraulic and Pneumatic Equipment
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE