A thorough experimental investigation of shock/shock interferences in highMach number flows

The Types III and IV interference flows, as defined by Edney, and correspon ding heat transfer distributions were investigated experimentally. The mode l consists of a cylindrically blunted plate and a wedge serving as an obliq ue shock generator. The 'thin wall' technique was used for heat transfer me asurements on the cylinder surface. These experiments were carried out in t he TsAGI short duration wind tunnel UT-l at Mach numbers 6 and 16 in air an d at Mach number 6.6 in carbon dioxide. The Reynolds number based on the pl ate bluntness diameter was varied in the range 2.2 x 10(4) to 1.6 x 10(6). Tests of the cylinder alone (without the wedge) at Mach number 6 and for di fferent Reynolds numbers revealed an influence of incoming disturbances on the stagnation line heat transfer. The influence of the impinging shock loc ation on the interference heat transfer was carefully investigated. Systema tic calculations of inviscid flow at Mach number 6 were also performed. Est imations of the maximum interference heat transfer rate, based on these cal culations and a boundary layer approach, compare well with the data. Influe nce of the specific heat ratio on the interference flow was studied. These experiments and calculations revealed important features of interference fl ow patterns and heat transfer distributions. (C) 2001 Editions scientifique s et medicales Elsevier SAS.