Effect of Thickness on the Lateral Force and Yawing Moment of a Sideslipping Delta Wing at Supersonic Speeds
Abstract
Calculations, based on linearized supersonic-flow theory and on the additional assumption that the Mach cones yaw with the wing, are made to determine the effect of thickness on the lateral force and yawing moment of a sideslipping delta wing at supersonic speeds. Generalized equations are derived for delta wings with rhombic profile and constant thickness ratio. Results indicate that, for wings suitable for supersonic flight, the contribution of wing thickness to the stability derivatives Cy(beta) and Cn(beta) (rates of change of lateral-force and yawing-moment coefficients with angle of sideslip) is small in comparison with the effects that may be expected from a vertical tail.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1949
- Accession Number
- ADA380718
Entities
People
- Kenneth Margolis
Organizations
- National Aeronautics and Space Administration