This paper presents results from a simplified experimental rig that aims to replicate the key physics of a transonic aircraft intake at high incidence for realistic altitudes. The equivalent flight conditions replicated are for free stream Mach numbers M_∞ = 0.25 -0.45 and incidence angles in the range α = 30 ± 5°. Measurement techniques from the simplified two-dimensional geometric setup include; schlieren imaging, surface oilflows, pressure sensitive paint, pressure and temperature measurements. CFD models that look to predict this behaviour have a limited accuracy largely due to a lack of experimental validation data - this lends itself as one of the key motivations for the work presented in this paper. Currently there is good qualitative agreement between the experimental results and the initial computation(s).
展开▼
