Subsonic Two-Dimensional-Flow Conditions Near an Airfoil Determined by Static Pressures Measured at the Tunnel Wall

Abstract

Static pressures existing in the neighborhood of the NACA 66,2-015 and NACA 66,2-2l5 airfoils in two-d1mensional flow were measured at Mach numbers between 0.300 and 0.800 in the Langley rectangular high-speed tunnel. These measurements were made by means of numerous orifices in the model end plate which was fitted flush with the tunnel wall. The investigation was conducted to determine the possibility of obtaining by this method the flow conditions in the region influenced by the model.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1949
Accession Number
ADA380649

Entities

People

  • Bernard N. Daley
  • Lillian E. Hanna

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundary Layer
  • Computational Fluid Dynamics
  • Contour Integrals
  • Equations
  • Flow
  • Flow Fields
  • Flow Separation
  • Incompressible Flow
  • Leading Edges
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Gradients
  • Shock Waves
  • Static Pressure
  • Two Dimensional
  • Two Dimensional Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.