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Numerical investigation of sonic jet injection effects on flow field structure and thrust vector control performance in supersonic nozzle
Mojtaba Tahani
1*Mohammad Hojaji
2Mohammad Salehifar
1Arash Dartoomian
1- Faculty of New Sciences and Technologies, University of Tehran, Tehran, Iran.
2- Aerospace Sciences and Technologies Institute, Tehran, Iran.
*P.O.B. 143951374 Tehran, Iran, [email protected]
A RTICLE I NFORMATION A BSTRACT
Original Research Paper Received 06 February 2015 Accepted 09 May 2015 Available Online 28 June 2015
Effects of secondary sonic jet injection in divergent part of supersonic nozzle on flow field structure and thrust vector control performance has been numerically analyzed. Three dimensional multi-blocks extended numerical code has been used to model the complexity of turbulence flow by k- SST model. Structured computational domain has been applied and the initial results of simulation were validated by the previous experimental result. Different injection power is generated by varying the injection surface and pressure ratio with respect to throat pressure. Injection power increment causes changes in performance and sometimes lowers it. In the current research, aside from description of complete complex flow features, allowable power range to increase system performance has been presented. In this range, increasing the injection mass flow rate decreases the amplification factor, but increases the deflection angle and axial thrust augmentation as the most important performance parameters. Out of estimated range for allowable mass power injection performance parameters behave differently, which demonstrates drastic drop in performance.
Keywords:
Thrust Vector Control Sonic Jet Injection Turbulent Flow Supersonic Nozzle
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