An Aerodynamic Investigation of a Low Aspect Ratio Wing.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
Pagination or Media Count:
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.
- Fluid Mechanics