The present study is aimed at presenting an experimental and numerical analysis of the flow patterns on the fore-body section of a sounding rocket model in the transonic regime. The experiments were carried out in the Pilot Transonic Wind Tunnel, known as TTP, of the Institute de Aeronautica e Espaco (IAE), in Sao Jose dos Campos, Brazil, for Mach numbers ranging from 0.6 to 1.0 and zero angle of attack, using the techniques of Pressure Sensitive Paint (PSP), pressure taps and the schlieren visualization method on a 1:34 scaled model of a sounding rocket. In order to gain more insights about the complex flow phenomena occurring in the transonic region, numerical simulations were also carried out Complex phenomena as shock waves, boundary layer deatachment, and expansion waves were clearly identified from the PSP pressure field and from the schlieren images. Good agreements between the PSP, pressure taps and numerical simulation results were observed.
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