Numerical Analysis of Fuel Injection Impacts on Thrust-Vectoring in a Dual Throat Nozzle

Document Type : Original Article

Authors

1 Assistant professor, Aerospace Research Institute, Tehran, Iran

2 PhD of Aerospace Engineering, Sharif University of Technology, Tehran, Iran

3 University of Shahid Satari, Tehran, Iran.

Abstract

Today, the Dual-throat Nozzles are known as one of the most effective approaches for fluidic thrust vectoring. The present study investigates the performance of a dual throat fluidic thrust-vectoring nozzle. The impacts of fuel secondary injection on performance parameters including discharge coefficient, system thrust ratio, pitch thrust-vector angle, pitch thrust-vectoring efficiency, thrust-to-mass-flow ratio and thrust-loss percentage are presented. Injection of seven different fuels including methane, ethane, propane, octane, diesel fuel, kerosene and gasoil have been investigated. Both reacting and non-reaction conditions have been studied. The results show that heavier fuels provide higher discharge coefficients. On the other hand, light fuels have higher thrust ratios. In the non-reacting conditions, diesel fuel and octane have the largest thrust-vector angle,. In general, light fuels offer a better performance in terms of thrust ratio, thrust-vectoring efficiency and thrust-to-mass-flow ratio, whereas heavy fuels have a better performance in terms of discharge coefficient, thrust-vector angle and thrust-loss percentage.

Keywords

Main Subjects


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