Design of Ducting, Hydraulic System Equipment and Instrumentation of Model 319A Boundary Layer Control Airplane

Abstract

A 0.6 scale wind tunnel model of the wing of the Cessna Model 319A Boundary Layer Control airplane was built and tested by the Universityof Wichita From this test data^the design of the wing and the circulation control system proceeded. The ducting was confined to the wing area aft of the rear spar. A full scale mock-up of the suction duct was constructed and tested by the University of Wichita. This design, utilizing the "constant area vortex" theory, produced excessive total pressure losses. After several successive modifications the suction duct was developed by the "constant loss" theory. This duct produced suitable distribution and quantity flow. The blowing duct was then designed on the basis of this same "constant loss" theory.

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Document Details

Document Type
Technical Report
Publication Date
Mar 23, 1956
Accession Number
AD0091128

Entities

People

  • W. D. Wise

Tags

DTIC Thesaurus Topics

  • Aircrafts
  • Airplanes
  • Axial Flow
  • Axial Flow Fans
  • Boundary Layer
  • Boundary Layer Control
  • Control Systems
  • Dynamic Pressure
  • Engineering
  • Hydraulic Equipment
  • Instrumentation
  • Military Research
  • Static Pressure
  • Test And Evaluation
  • United States
  • Wind Tunnel Models
  • Wind Tunnels

Readers

  • Aerodynamics/Aeronautics.
  • Combustion and Flow Dynamics.