A Program for Computing the Pressure Distribution and Aerodynamic Coefficients for Cambered Thin Supersonic Wings of Arbitrary Planform with Subsonic Leading Edges.
Abstract
AEROBALLISTICS DIRECTORATEA Program for Computing the Pressure Distribution and Aerodynamic Coefficients for Cambered Thin Supersonic Wings of Arbitrary Planform with Subsonic Leading Edges.Technical rept.,Van Buren,Bruce L. ;RD-73-24DA-1-M-262303-A-214*Supersonic airfoils, Leading edge, Pressure, Distribution, Aerodynamic characteristics, Mathematical models, Digital simulationThe computer solution to the linearized potential flow equations which gives a reasonably accurate description of the pressure distribution for thin cambered supersonic wings with subsonic leading edges is presented. The program will compute the aerodynamic coefficients associated with the pressure distribution such that comparison can be made of the aerodynamic characteristics between a flat wing and a cambered wing at small angles of attack. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 05, 1973
- Accession Number
- AD0772952
Entities
People
- Bruce L. Van Buren
Organizations
- United States Army Aviation and Missile Command