Publicou 6 edições por ano
ISSN Imprimir: 1948-2590
ISSN On-line: 1948-2604
EXPERIMENTAL STUDY OF TANGENTIAL BLOWING EFFECT OF SUPERSONIC JET ON AERODYNAMICS OF A SUPERCRITICAL WING AT TRANSONIC SPEEDS
RESUMO
The results of experimental studies of tangential jet blowing efficiency for improvement of supercritical wing aerodynamics at transonic speeds are presented. The studies of the wing-fuselage model were performed in the TsAGI T-106 transonic wind tunnel in Mach number ranges of M = 0.4−0.8, Reynolds number ranges of Re = (1.4−2.2)106, and angles-of-attack α = −2°−15°. The effects of jet blowing intensity on lift, pitching moment, and drag of the model, and also on the pressure distribution at the wing middle section are examined. The values of jet momentum coefficient, required for shock-induced flow separation suppression at transonic speeds, are determined. It is shown that at Mach number M = 0.78 tangential jet blowing with low intensity (Cμ = 0.003−0.005) increases the maximum lift-to-drag ratio values of the wing-fuselage model by 10% approximately.