Characteristics of Thin Triangular Wings With Constant-Chord Partial-Span Control Surfaces at Supersonic Speeds
Abstract
A theoretical analysis was male of the characteristics of constant-chord partial-span control surfaces on thin triangular wings at supersonic speeds by use of methods based on the linearized theory for supersonic flow. Two cases were treated: In one the flap was considered to extend outboard from the center of the wing and in the other the flap was considered to extend inboard from the wing tip. Expressions were found for the lift coefficient, rolling- moment coefficient, and hinge-moment coefficient due to flap deflection, the hinge-moment coefficient due to angle of attack, and the hinge-moment coefficient due to flap lift. A few figures are given to illustrate the application of the equations.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1948
- Accession Number
- ADA380750
Entities
People
- Robert L. Nelson
- Warren A. Tucker
Organizations
- National Aeronautics and Space Administration