Multi-Directional Co-Flow Fluidic Thrust Vectoring Intended for a Small Gas Turbine

An investigation of empirical formulation and design optimisation of co-flow fluidic thrust vectoring nozzles

“…All the blocks are discretised with structured grid and grid dependency is also investigated by verifying the variation of the results from the coarse to the fine grid. Actually, both the control volume and the grid independency checks were performed, based on the authors' previous experiences by the rectangular and a simple circular nozzles (15,19) . Here, a parameter named meshsize was defined in the journal file (glyph) to automatically change the whole mesh pattern for the independency checks.…”

“…Secondary flow and thrust deflection are particularly shown in this view. Validation of the CFD simulation by experimental results and thermal images is presented in references by means of identification and quantification of errors (15,19) . The next part presents how to investigate an optimal geometry for the Coanda surface by the Quasi-Newton optimisation method.…”

“…3 and listed in Table 2, different nozzles including one rectangular and two circular sections have been built and experimentally tested to gather data for different secondary to primary mass flow ratios. To improve the validity of the results by increasing the number of data, other geometrically different nozzles have also been considered, some of which from a parallel investigation process on the nozzle geometry optimisation for the best thrust vectoring angle, and analysed computationally using a previously developed and validated CFD simulation models (15,19) . The validation of the models has been carried out by the use of the experimental test data of the already mentioned physically built nozzles.…”

Modelling and robust control of fluidic thrust vectoring and circulation control for unmanned air vehicles

“…It should be noted that the FTV arrangement described above can be used to achieve moderate thrust vectoring performance only for low subsonic primary exhaust jet Mach numbers. For high primary exhaust jet Mach numbers, supersonic secondary flow is required for adequate control effectiveness [10]. In the case of DEMON, co-flow arrangement is still useful, since the cruise speed range is 22-72 m/s.…”

“…Both techniques use the phenomenon of Coanda jet attachment to convexly curved surfaces to enable either efficient control of a primary jet using a secondary jet (FTV) or to eject a tangential jet over a rounded trailing edge for boundary layer control (CC) [6] (see Figs 1 and 2). Some of the approaches to FTV include the shock thrust vector control method [7] and fluidic throat skewing [8] for supersonic jets, the counterflow technique for both subsonic and supersonic jets [9] and co-flow technique for subsonic jets [10]: the reader is referred to reference [11] for a more detailed account of FTV techniques. The co-flow technique in particular is actively explored for use in subsonic aircraft because of its ease of implementation and effectiveness.…”