The Unsteady Computerized Thermographic Technique (UCTT) provides patterns of the Stanton number on a body surface. These patterns are the imprints of the flow field. The UCTT already proved to be a powerful, not intrusive diagnostic tool both for the visualization and the strength evaluation of vortical structures on the lee-side surface of delta wing models. The patterns are obtained by processing, by an "ad hoc" mathematical model, the temperature time evolution of the model surface. The temperature is measured at a distance by a thermocamera. In previous tests on delta wing models, the used thermocamera showed a limitation in the optics and did not provide an appropriate space resolution and, therefore, a detailed visualization of whole vortical structure. In the present paper this limitation has been overcome. The optics improvement has doubled the space resolution of thermocamera. Tests, made at angle of attack of 6-deg. and Mach number of 1.92, verified that this improvement was substantial. In fact, the detection of secondary vortex on delta wing model and strake vortices on a double delta wing model was made possible. Unfortunately, it was not possible to visualize details of vortical structure on a Gothic wing model. Tests showed that vortical patterns were similar to the one on delta wing model.
Nomenclature: C chord, m C specific heat of material, J/(kgK) Cp specific heat of air at constant pressure, J/(kgK) k thermal conductivity, W/(mK) M Mach number q convective heat flux, W/m 2 Re Reynolds number, Vc/v St Stanton number, (Eq.1) T temperature, K V velocity, m/s x distance along the wing chord, m y distance along the wing span, m Greek symbols a angle of attack L1 finite interval o plate thickness, m E surface emissivity v kinematic viscosity of air, W/(mK) 60 p (J' r Visualizing Strake and Wing Vortices in Supersonic Flow by a Thermographic Technique densityof air, kg/m" Stefan-Boltzman constant, 5.67X 10-8 W/(m 2K4 ) observation durationtime, s Subscrits a ambient aw adiabatic wall o outer surfaceof the calorimetric plate T thermal w wall free stream