High-Speed Wind-Tunnel Tests of Gun Openings in the Nose of the Fuselage of a 1/4-Scale Model

Abstract

In connection with recent tests of a 1/4-scale model pursuit airplane in the NACA 8-foot high-speed tunnel. Gun openings having low drag were developed for installation in the nose of the fuselage. The increase in the fuselage-drag coefficient for the final form of openings was 0.0132 at a Mach number of 0.69 and at an angle of attack of 0 deg. The corresponding drag coefficient based on the wing area was about 0.0005. The critical speed of the airplane was not affected by the gun openings.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1942
Accession Number
ADB807295

Entities

People

  • Henry A. Fedziuk

Organizations

  • National Advisory Committee for Aeronautics

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aircrafts
  • Airplanes
  • Boundary Layer
  • Coefficients
  • Drag
  • Dynamic Pressure
  • Fuselages
  • Guns
  • Inboard
  • Laminar Boundary Layer
  • Mach Number
  • Machine Guns
  • Pressure Measurement
  • Scale Models
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • ballistics.