Wind-Tunnel Investigation of Wing Inlets for a Four-Engine Airplane

Abstract

Wind-tunnel investigation was conducted to further the development of leading-edge wing inlets. Aerodynamic tests of the basic wing and the original inlet were also made. The original inlet was found to decrease the maximum lift coefficients and to have critical Mach numbers below those of the wing with the basic nose installed. The total pressure recovery in the oil cooler ducts was poor, regardless of the inlet installation. Two inlets were developed that should be satisfactory for a 4-engine airplane.

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Document Details

Document Type
Technical Report
Publication Date
Mar 11, 1947
Accession Number
ADA801415

Entities

People

  • Edwin B. Goral
  • Walter A. Bartlett Jr.

Organizations

  • National Advisory Committee for Aeronautics

Tags

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Air Intakes
  • Aircrafts
  • Airplanes
  • Altitude
  • Boundary Layer
  • Coefficients
  • Inlets
  • Leading Edges
  • Mach Number
  • Oil Coolers
  • Pressure Distribution
  • Pressure Measurement
  • Static Pressure
  • Wind Tunnels
  • Wing Flaps
  • Wing Inlets

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerodynamics/Aeronautics.
  • Aerospace Engineering