The 8 m x 6 m Low Speed Wind Tunnel at the Chinese Aerodynamic Research and Development Center,

Abstract

This low speed wind tunnel at CARDC is a large scale, double experimental section wind tunnel solely designed and built in China. It is primarily used for experiments in the aerodynamic characteristics of airplanes and other aircraft; in ground wind load of guided missiles and space vehicles; in large attack angle of airplanes and guided missiles; in large prototypes; in aerodynamics of helicopters and vertical short takeoff aircraft; and in industrial aerodynamics (e.g., architecture, bridges, fans and automobiles. It passed national certification at the end of 1983 and was officially released for use. This wind tunnel is an open-circuit, closed double experimental section in series, large scale low speed wind tunnel. Its entire length is 237 m with a maximum width of 40 m and a maximum height of 20.5 m. It consists of air intake assembly, stabilization section, first convergence section, first experimental section, second experimental section, first divergence section, fan section, second divergence section, and air exhaust assembly.

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Document Details

Document Type
Technical Report
Publication Date
May 30, 1986
Accession Number
ADA168448

Entities

People

  • Maoxum Wang
  • Ruikang Pan

Organizations

  • National Air and Space Intelligence Center

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes
  • Sensors
  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Aerodynamic Characteristics
  • Aircrafts
  • Airframes
  • Airplanes
  • Control Systems
  • Electric Motors
  • Flow
  • Flow Fields
  • Foreign Technology
  • Guided Missiles
  • Measurement
  • Pressure Measurement
  • Short Takeoff Aircraft
  • Standards
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Engineering

Readers

  • Aerospace Engineering
  • Fluid Dynamics.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster
  • Space - Spacecraft Maneuvers