The Theoretical Characteristics of Triangular-Tip Control Surfaces at Supersonic Speeds. Mach Lines Behind Trailing Edges
Abstract
By means of linearized theory, generalized expressions in closed form have been obtained for the characteristics due to control-surface deflection (C sub L Delta), (C sub l Delta), (C sub m Delta), and (C sub h Delta) and due to wing angle of attack (C sub h alpha) for wing plan forms having triangular-tip control surfaces at supersonic speeds. The analysis considers wing trailing-edge sweep, control-surface geometry, and Mach number for the deflection characteristics. For (C sub h alpha) the effects of wing leading-edge sweep and aspect ratio are also included. The analysis is limited to configurations where the trailing edges are supersonic and where the innermost Mach line from the leading edge of the control-surface root chord does not intersect the wing root chord. Charts are presented for the deflection characteristics for configurations having the sweep of the wing and control-surface trailing edges equal and for the location of the hinge line for balanced controls. Tables of calculations are given for configurations in which the wing and flap trailing edges are unequally swept. The results of the analysis show that the effects of wing trailing-edge sweep on (C sub L Delta), (C sub l Delta), and (C sub m Delta) are more significant than the effects of control-surface trailing-edge sweep ((C sub h Delta) is not affected by the wing trailing-edge sweep). Aileron reversal may occur for certain conditions when the control-surface leading edges are subsonic. Maximum rolling moments are obtained for control surfaces having supersonic leading edges.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1952
- Accession Number
- ADA378303
Entities
People
- Julian H. Kainer
- Mary D. King
Organizations
- National Aeronautics and Space Administration