TRANSITION OF THE LAMINAR BOUNDARY LAYER ON A DELTA WING WITH 74 DEGREE SWEEP IN FREE FLIGHT AT MACH NUMBERS FROM 2.8 TO 5.3

Abstract

The test were conducted at Mach numbers from 2.8 to 5.3, with model surface temperatures small compared to boundary-layer recovery temperature. The effects of Mach number, unit Reynolds number, leading-edge diameter, temperature ratio,AND ANGLE OF ATTACK WERE INVESTIGATED IN AN EXPLORATORY FASHION. The results were compared to results of wind-tunnel tests of swept wings and to results f free-flight tests for unswept leading edges. (Author)

Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1961
Accession Number
AD0261196

Entities

People

  • Gary T. Chapman

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Delta Wings
  • Flight
  • Free Flight
  • Laminar Boundary Layer
  • Layers
  • Leading Edges
  • Mach Number
  • Reynolds Number
  • Surface Temperature
  • Swept Wings
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Mechanics and Fluid Dynamics.