Accession Number:

AD0772952

Title:

A Program for Computing the Pressure Distribution and Aerodynamic Coefficients for Cambered Thin Supersonic Wings of Arbitrary Planform with Subsonic Leading Edges.

Descriptive Note:

Technical rept.,

Corporate Author:

ARMY MISSILE COMMAND REDSTONE ARSENAL ALA AEROBALLISTICS DIRECTORATE

Personal Author(s):

Report Date:

1973-08-05

Pagination or Media Count:

73.0

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-214Supersonic 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

Subject Categories:

  • Aerodynamics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE