A COMPARISON OF THE THEORETICAL DETERMINATION OF THE DEVELOPMENT OF THE BOUNDARY LAYER MOMENTUM THICKNESS IN AN ARBITRARY PRESSURE GRADIENT WITH FULL- SCALE FLIGHT EXPERIMENTS ON A POROUS AIRFOIL SECTION WITH TRANSPIRATION

Abstract

Calculation of the turbulent boundary layer momentum thickness around a NACA 4416 airfoil section was made by a successive approximation method developed for two-dimensional and axisymmetric flows. These results are compared with experimental results obtained from flight tests with a sailplane--Schweizer TG-3--with reasonable results.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1965
Accession Number
AD0620246

Entities

People

  • Hideki Yamaoka
  • J. J. Cornish Iii

Organizations

  • Mississippi State University

Tags

Communities of Interest

  • Air Platforms
  • Ground and Sea Platforms
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Abstracts
  • Aircrafts
  • Army Aviation
  • Boundary Layer
  • Boundary Layer Control
  • Equations
  • Experimental Data
  • Flow
  • Fluid Mechanics
  • Gliders
  • Government Procurement
  • Leading Edges
  • Measurement
  • Pressure Distribution
  • Pressure Gradients
  • Skin Friction
  • Turbulent Boundary Layer

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.