Flow patterns on a NACA 0012 for high angle of attack
Henrique Fanini Leite1; João Batista Falcão Filho2; Ana Cristina Avelar2; Roberto Gil Annes da Silva1
1 Instituto Tecnológico de Aeronáutica; 2 Instituto de Aeronáutica e Espaço
doi:10.20906/CPS/COB-2015-2393
Resumo
The purpose of the present study is to investigated the flow patterns on NACA 0012 profile for high angles of attack, for example α equal to 5 degrees. The study will be conducted in The experiments will be conducted in the Pilot Transonic wind tunnel of the Instituto de Aeronáutica e Espaço (IAE), TTP. This facility allows aerodynamic tests in Mach number varying from 0.2 to 1.3 with automatic controls of pressure (from 0.5 bar to 1.2 bar), temperature and humidity. The flow in its test section of 0.25 m x 0.30 m is continuously driven by a main two-stage axial compressor of 830 kW. A NACA 0012 profile, made of aeronautical aluminum with a chord of 65.5 mm will be considered. This investigation is an initial study with the final purpose of analyzing the non-stationary flow in situation of separated flow on a NACA 0012 profile for low mach numbers, around 0.4-0.5. The initial tests will be conducted for the situation of stationary flow using the technique of pressure sensitive paint (PSP), considering a stationary flow, and compared with the existent results in the literature. The next step is to carry out the same experiment using the PSP technique of fast response, fast-PSP. The scope of the present study is just the analysis in the stationary regime, a comparison with results from numerical simulations in the literature and a discussion of the physical phenomena investigated.
Palavras-chave: Transonic wind tunnel; NACA 0012