Accession Number:

AD0091128

Title:

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

Descriptive Note:

[Technical Report, Technical Report]

Corporate Author:

CESSNA AIRCRAFT CO WICHITA KS

Personal Author(s):

• Wise, W. D.

Report Date:

1956-03-23

Pagination or Media Count:

63

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 datathe 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.

Descriptors:

Subject Categories:

• Aircraft
• Fluid Mechanics

Distribution Statement:

[A, Approved For Public Release]