SUBSONIC INVESTIGATION OF EFFECTS OF BODY IDENTATION ON ZERO-LIFT DRAG CHARACTERISTICS OF A 45 deg SWEPTBACK WING-BODY COMBINATION WITH NATURAL AND FIXED BOUNDARY LAYER TRANSITION THROUGH A RANGE OF REYNOLDS NUMBER FROM 1 X 10 6 TO 8 X 10 6

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Document Details

Document Type
Technical Report
Publication Date
Apr 05, 1954
Accession Number
AD0029199

Entities

People

  • Albert L. Braslow
  • Gene J. Bingham

Organizations

  • Langley Research Center

Tags

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aspect Ratio
  • Boundary Layer
  • Boundary Layer Transition
  • Flow
  • Laminar Boundary Layer
  • Laminar Flow
  • Layers
  • Leading Edges
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Reynolds Number
  • Roughness
  • Sweptback Wings
  • Turbulent Flow
  • Wing Body Configurations