Accession Number:

AD0774571

Title:

An Investigation of the Trailing Vorticity Behind a STOL Aircraft.

Descriptive Note:

Final rept., Sep 71-Aug 73,

Corporate Author:

MISSISSIPPI STATE UNIV STATE COLLEGE DEPT OF AEROPHYSICS AND AEROSPACE ENGINEERING

Personal Author(s):

• Mertaugh,Lawrence J.
• Damania,Rustom B.

Report Date:

1973-12-01

Pagination or Media Count:

109.0

Abstract:

The report presents the results of a test program to measure the near-field wake behind the wing of a test aircraft, out of the ground effect, and to obtain vortex trajectory data on trailing vortices generated within the ground effect. The test aircraft was a high-lift L-19 aircraft incorporating a distributed-suction boundary layer control system. The wake measurement probe was supported from the fuselage of the test aircraft and was mounted on a trolley which moved along a boom structure. The velocity measurements were made with a six-element hot-film anemometer. The near field wake data were obtained in two measurement planes located 0.64 and 5.10 feet behind the wing. Data were obtained at zero and fullflap deflection and true speeds of 46, 66, and 85 mph. The data are presented as contours of constant normalized vorticity, nondimensional vertical velocity, and non-dimensional longitudinal velocity increment within the measurement planes. Modified author abstract

Descriptors:

• *Short takeoff aircraft
• *Vortices
• Wake
• Ground effect
• Flow visualization
• Flow fields
• Near field
• Instrumentation

Subject Categories:

• Aerodynamics
• VSTOL

Distribution Statement:

APPROVED FOR PUBLIC RELEASE