Analysis of the flow patterns on the fore-body section of a sounding vehicle in the transonic regime
The present study has the purpose of presenting a numerical and experimental analysis of the flow patterns on the fore-body section of a sounding rocket model in the transonic regime. The measurements were carried out in the Pilot Transonic Wind Tunnel, known as TTP, at the Instituto de Aeronáutica e Espaço (IAE), in São José dos Campos, Brazil, for Mach numbers ranging from 0.6 to 1.06 and zero angle of attack. The experimental techniques of pressure taps, pressure-sensitive paint (PSP) and schlieren visualization method were performed on a 1:34 scaled model of a sounding rocket. Complex phenomena as shock waves, boundary layer detachment, 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, except around the tip of the model because of the curvature and also in details that were not captured by the camera.
KeywordsTransonic Wind Tunnel Pressure-Sensitive Paint Sounding Rocket
The first author thanks to the São Paulo Research Foundation (FAPESP) through the process 2014/06790-6 and National Council for Scientific and Technological Development (CNPq) through the process 402233/2013-1 and 308829/2015-8 (DT). The authors thanks also FAPESP through the process 2013/23690-2, aimed at repairing the TTP compressor blades and CAPES trough Pró-estratégia Project num. 20, Edital 50/2011.
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