Influence of disturbances generated by the nozzle boundary layer on the heat exchange on the cylindrical nose of a body in a hypersonic flow

The heat transfer to a cylindrical surface whose generators are perpendicular to the freestream direction is investigated. Experiments were carried out in a short-duration wind tunnel at Mach numbers M=6 and 16. At M=6, the Reynolds number based on the cylinder diameter was varied on the range from 2.2·104 to 0.95·106 for the purpose of studying the effect of acoustic disturbances generated by the nozzle boundary layer on the heat exchange.