Pressure Distribution on the Fuselage of a Midwing Airplane Model at High Speeds

Abstract

Pressure distribution data useful in the structural design of air scoops, vents, and various fuselage parts were obtained in wind-tunnel tests at speeds of 140 to 400 mph at lift coefficients ranging from -0.2 to 1.0. Highest negative pressure on fuselage occurred near the wing. Results indicate that the critical speed of fuselage will be decreased by wing-induced velocities.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1943
Accession Number
ADB806581

Entities

People

  • James B. Delano

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Airplanes
  • Bomb Bays
  • Classification
  • Coefficients
  • Compressive Properties
  • Fineness Ratio
  • Fixed Wing Aircraft
  • Fuselages
  • Mechanics
  • Motion
  • Physics
  • Pressure Distribution
  • Two Dimensional
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion and Flow Dynamics.