Accession Number:

ADA021733

Title:

An Aerodynamic Investigation of a Low Aspect Ratio Wing

Descriptive Note:

[Technical Report, Master's Thesis]

Corporate Author:

AIR FORCE INSTITUTE OF TECHNOLOGY WRIGHT-PATTERSON AFB OH

Personal Author(s):

• McCommon, Leonard V.

Report Date:

1975-12-01

Pagination or Media Count:

126

Abstract:

The study consisted of modeling and testing a high-speed, low aspect ratio flying wing no conventional center body or fuselage to determine its lift, drag, and static stability characteristics at Mach numbers of 0.70 to 0.86. Six different configurations of stabilizing fins were tested along with the basic finless configuration. Wind tunnel test results are presented in graphic and tabular form for use in further design studies.

Descriptors:

• aerodynamic characteristics
• aerodynamic configurations
• aircrafts
• air force
• boundary layer
• pressure distribution
• wind tunnels
• airfoils
• geometry
• measurement
• mechanics
• wind tunnel tests
• air force facilities
• bending stress
• center of gravity
• computer programs
• flow visualization

Subject Categories:

• AERODYNAMICS
• Fluid Mechanics

Distribution Statement:

[A, Approved For Public Release]