Abstract
The application of the Shock Vector Control (SVC) approach to an axysimmetric supersonic nozzle is studied numerically. SVC is a Fluidic Thrust Vectoring (FTV) strategy that is applied to fixed nozzles in order to realize jet-vectoring effects normally obtained by deflecting movable nozzles. In the SVC method, a secondary air flow injection close to the nozzle exit generates an asymmetry in the wall pressure distribution and side-loads on the nozzle, which are also lateral components of the thrust vector. SVC forcing of the axisymmetric nozzle generates fully three-dimensional flows with very complex structures that interact with the external flow. In the present work, the experimental data on a nozzle designed and tested for a supersonic cruise aircraft are used for validating the numerical tool at different flight Mach numbers and nozzle pressure ratios. Then, an optimal position for the slot is sought and the fully 3D flow at flight Mach number M∞=0.9 is investigated numerically for different values of the SVC forcing.
Highlights
Fixed Axisymmetric SupersonicThrust Vectoring (TV) consists of the modulation of the thrust vector in a variable direction other than the axial direction, introducing an additional control variable in the equation of motion of the aircraft
The resulting effect is a side-force on the nozzle that can be seen as the lateral component of the thrust vector
We follow the same path and numerically analyze the Shock Vector Control (SVC) effects of secondary mass flow injection on the nozzle side force, in the presence of an external flow. At this stage, we focused on the study of the effectiveness of the Fluidic Thrust Vectoring (FTV) for different levels of forcing, based on different SMF values, at the nozzle pressure ratio nozzle pressure ratios (NPR) = 7.08 and with an external flow Mach number M∞ = 0.9
Summary
Thrust Vectoring (TV) consists of the modulation of the thrust vector in a variable direction other than the axial direction, introducing an additional control variable in the equation of motion of the aircraft. The same effect can be obtained without actuated mechanical hardware, by forcing and manipulating the flow inside a nozzle of fixed geometry This second approach, namely the Fluidic Thrust Vectoring (FTV), uses a secondary air bleed in order to actively manipulate and control the primary air-stream of the nozzle. The FTV performances of an axisymmetric nozzle under shock vector control are investigated numerically. The numerical tools are validated with respect to experimental data [27] in the axisymmetric case for different values of the Nozzle Pressure Ratio NPR and different Flight Mach numbers. The SVC approach is applied to the fully three-dimensional case and the nozzle FTV effectiveness and performances are investigated numerically for different values of the secondary mass flow
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