Historical review and future perspectives for pilot transonic wind tunnel of IAE

Filho, João Batista Pessoa Falcão; Avelar, Ana Cristina; Reis, Maria Luísa Colucci da Costa

doi:10.5028/jatm.2009.01011927

Cited by 11 publications

(2 citation statements)

References 3 publications

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“…Its test section is 30 cm wide and 25 cm high, with slotted walls. The tunnel has automatic controls of pressure (from 0.5 bar to 1.25 bar), Mach number (from 0.2 to 1.3), temperature and humidity, related to test section (Falcão Filho et al, 2009). Figure 4 shows a partial view of the TTP's aerodynamic circuit.…”

Section: Description Of the Experimentsmentioning

confidence: 99%

Evaluation of the Effects of Illumination, Temperature and Painting Finish in PSP Technique

Costa

Avelar

Filho

2013

RETERM

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This paper reports the results of global pressure measurements on a NACA0012 profile, obtained with the Pressure Sensitive Paint technique (PSP), and compares them with conventional pressure tap measurements with the purpose of analyzing the influence of parameters as illumination efficiency and temperature variation of the air flow in the accuracy of the PSP experimental results. The experimental measurements were conducted in the Pilot Transonic Wind Tunnel (TTP) of the Instituto de Aeronáutica e Espaço (IAE) for Mach number values of 0.4, 0.6 and 0.8. The experiments showed that in a carefully prepared experiment, under appropriated operational conditions, and rigorous adjustments of the PSP components, the obtained results can be accurate. Moreover, even when the influence of temperature is significant and the illumination condition is not ideal, it was possible to estimate well the impact caused in the pressure distribution over the model surface.

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Section: Description Of the Experimentsmentioning

confidence: 99%

Evaluation of the Effects of Illumination, Temperature and Painting Finish in PSP Technique

Costa

Avelar

Filho

2013

RETERM

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“…The transonic wind tunnel would be driven not only by a main compressor (continuously) but also by an injection system (intermittently), which would help to enlarge the operational tunnel envelope, without penalizing the installed power. Because of this new feature, a pilot transonic facility was also conceived in order to test this challenging idea (Falcão Filho et al 2009). For several reasons, mostly related to budget restrictions, only the pilot facility design was completely built and it became fully operational in 2002.…”

Section: The Pilot Transonic Wind Tunnelmentioning

confidence: 99%

Visual Experimental and Numerical Investigations Around the VLM-1 Microsatellite Launch Vehicle at Transonic Regime

Mata¹,

Filho²,

Avelar³

et al. 2017

J.Aerosp. Technol. Manag.

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It is performed and presented an experimental and numerical investigation over the flow patterns around the forebody section of a microsatellite launch vehicle in development at Instituto de Aeronáutica e Espaço. The experimental investigation with a VLM-1 model in 1:50 scale is carried out at the Brazilian Pilot Transonic Wind Tunnel, located in the Aerodynamics Division of the mentioned Institute, using the classical schlieren flow visualization technique. Schlieren images are obtained for nominal Mach number varying from 0.9 to 1.01. Numerical simulation using Stanford's SU2 code is conducted together with the experimental investigation in order to improve the understanding of the complex physical phenomena associated with the experimental results of this particular regime. The combination of the 2 techniques allowed the assessment of some important aspects on the flow field around the vehicle in the conditions considered in this study, such as shock wave/boundary-layer interaction. The numerical simulation is also very important, allowing the quantification of some important parameters and confirming the shock wave formation patterns observed in the simulation when compared with the schlieren images. A good agreement regarding the position of the shock wave, when compared with the schlieren images, with a maximum error of about 6%, is observed over the VLM model.

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Analysis of the flow patterns on the fore-body section of a sounding vehicle in the transonic regime

Avelar

Basso

Filho

et al. 2018

J Braz. Soc. Mech. Sci. Eng.

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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.

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Historical review and future perspectives for pilot transonic wind tunnel of IAE

Cited by 11 publications

References 3 publications

Evaluation of the Effects of Illumination, Temperature and Painting Finish in PSP Technique

Evaluation of the Effects of Illumination, Temperature and Painting Finish in PSP Technique

Visual Experimental and Numerical Investigations Around the VLM-1 Microsatellite Launch Vehicle at Transonic Regime

Analysis of the flow patterns on the fore-body section of a sounding vehicle in the transonic regime

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