INVESTIGATION OF IMPULSE-TYPE SUPERSONIC COMPRESSOR WITH HUB-TIP RATIO OF 0.6 AND TURNING TO AXIAL DIRECTION 1 - PERFORMANCE OF ROTOR ALONE

Open PDF

Document Details

Document Type
Technical Report
Publication Date
May 06, 1954
Accession Number
AD0030124

Entities

People

  • Ward W. Wilcox

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Back Pressure
  • Boundaries
  • Boundary Layer
  • Compressor Rotors
  • Compressors
  • Deceleration
  • Flow
  • Geometry
  • Guide Vanes
  • Inlet Guide Vanes
  • Leading Edges
  • Mach Number
  • Measurement
  • Measuring Instruments
  • Pressure Distribution
  • Shape
  • Static Pressure

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow