Accession Number : AD0092632


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


Corporate Author : MASSACHUSETTS INST OF TECH CAMBRIDGE GAS TURBINE LAB


Personal Author(s) : Moore, Jr , Raymond W ; Richardson, David L


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/092632.pdf


Report Date : Oct 1955


Pagination or Media Count : 62


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