The Investigation for the Aerodynamic and Heat Transfer Characteristics of Slender Hypersonic Cones over a Wide Range of Angles of Attack.

摘要

The problems of aerodynamic and heat transfer characteristics of slender sharp nosed hypersonic cones over a wide range of angles of attack are examined and the analytical solutions are presented. Three particular problems are studied: (1) inviscid flow characteristics of shock layer involving laminar separation in the leeward side with undisturbed free stream Mach number 7.95and angle of attack 20degrees for cone half angle 10degrees, (2) attached three-dimensional compressible boundary layer over the cone, (3) aerodynamic and heat transfer characteristics of turbulent separated flow. (Author)