Fluidic Jet Vectoring at Subsonic Flow ay Using Counter Flow Method
Experimental & Computational and investigations of thrust vectoring by using counter flow method had been carried out in the present work. The experimental investigation included design and construction of test rig with rectangular duct with aspect ratio of (4.4) in order to investigate the effect of various geometric variables on thrust vectoring angle. Set of experiment at tests was carried out over the mass flow ratio (Ṁs/Ṁp) range 0 ≤ (Ṁs/Ṁp) ≤ 0.31 with secondary slot gap height g/H= (0.0294, 0.0588, 0.088 and 0.1176) and coanda surface diameter R/H= (1.176, 2.353, 3.529and 4.705).
Load measurements were obtained using four load cells. The computational investigation involved a 3D numerical solution by FLUENT Software for some of experimental cases.
Experimental results show that the increase in secondary jet blowing rate lead to increasing in the jet vectoring angle, there are three zone can be observed, dead zone appears at low mass flow ratios, then followed by control region in which continuous thrust vector control can be achieved followed by a saturation region. The length of the dead zone‟ was also dependent on the size of the
Coanda surface diameter which a small diameter resulted in a prolonged „dead zone‟ range, and the secondary gap height to the primary gap height had inverse relation with jet vectoring angle. The investigation shows that both the experimental and computational results obtained follow a similar trend line. Mach number is less than 0.5.
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