Accession Number:

ADA048898

Title:

An Aerodynamic Investigation of a Forward Swept Wing

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1977-12-01

Pagination or Media Count:

115.0

Abstract:

This study consisted of modeling and wind tunnel testing of a high speed, subsonic, low aspect ratio, forward swept wing with an advanced supercritical airfoil section for the purpose of determining its lift, drag, and pitching moment characteristics as compared to a similar aft swept wing. Tests were conducted at Mach numbers of 0.63 to 0.93 in the Air Force Flight Dynamics Laboratorys Trisonic Gasdynamic Facility located at Wright-Patterson Air Force Base, Ohio. Two wing configurations, forward and aft swept, were tested and compared to computer predictions provided by the Unified Subsonic-Supersonic Program Woodwards Version B. The results indicated that the forward swept wing was capable of higher useable angles of attack while maintaining a lower drag coefficient for angles of attack below eight degrees. Wind tunnel test results are presented in graphical and tabular form for use in future design studies of similar aerodynamic configurations.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE