Accession Number : AD0267914

Title :   Second-Order Theory for a Thin Wing in Supersonic Flow with a Weak Spanwise Entropy Gradients,

Corporate Author : AERONAUTICAL RESEARCH INST OF SWEDEN STOCKHOLM

Personal Author(s) : WILBY,PETER G.

Report Date : JUN 1961

Pagination or Media Count : 1

Abstract : The three-dimensional perturbation velocities over an infinite thin wing with a sharp leading edge in non-uniform supersonic flow are derived and used to investigate the second-order contribution to the pressure coefficient on a wing surface, due to a spanwise entropy gradient. Pressure distributions are calculated for a wedge section wing at various Mach numbers for probable values of entropy gradient. Results show that entropy gradient effects can be important. Procedure for application of the theory is given for the case of a wing situated behind the curved shock generated by a blunt nosed body. (Author)

Descriptors :   *SUPERSONIC FLOW, *WINGS, AERODYNAMIC CONFIGURATIONS, BLUNT BODIES, ENTHALPY, ENTROPY, EQUATIONS, GAS FLOW, PARTIAL DIFFERENTIAL EQUATIONS, PERTURBATION THEORY, POTENTIAL THEORY, SHOCK WAVES, THERMODYNAMICS, VORTICES

Distribution Statement : APPROVED FOR PUBLIC RELEASE