scholarly journals Computational Study of an Axisymmetric Dual Throat Fluidic Thrust Vectoring Nozzle for a Supersonic Aircraft Application

2007 ◽  
Author(s):  
Karen Deere ◽  
Jeffrey Flamm ◽  
Bobby Berrier ◽  
Stuart Johnson
Keyword(s):  
Computational Study ◽  
Thrust Vectoring ◽  
Supersonic Aircraft ◽  
Fluidic Thrust Vectoring ◽  
Aircraft Application

Experimental and Numerical Investigations of a Bypass Dual Throat Nozzle

2014 ◽  
Vol 136 (8) ◽  
Author(s):  
Rui Gu ◽  
Jinglei Xu ◽  
Shuai Guo
Keyword(s):  
Computational Study ◽  
Minimum Area ◽  
Thrust Vectoring ◽  
Thrust Vector ◽  
Vector Angle ◽  
Vectored Thrust ◽  
Fluidic Thrust Vectoring ◽  
Secondary Injection ◽  
Maximum Thrust ◽  
Thrust Performance

The bypass dual throat nozzle (BDTN) is a new kind of fluidic vectoring nozzle. A bypass is set between the upstream convergent section and upstream minimum area based on the conventional dual throat nozzle (DTN). The BDTN shows a minimum or even no penalty on the nozzle's thrust performance, while it would be able to produce steady and efficient vectoring deflection similar to the conventional DTN. A BDTN model has been designed and subjected to experimental and computational study. The main results show that: (1) BDTN does not consume any secondary injection from the other part of the engine, while it can produce steady and efficient vectoring deflection. (2) Under the same condition, it can provide the maximum thrust vectoring efficiency of all the known fluidic thrust vectoring concepts reported in the literature. (3) The thrust vector angle is also greater than that of the conventional DTN that has been reported up to now. Especially, under NPR = 10, the thrust vector angle of BDTN can reach 21.3 deg. (4) For a wide NPR range from 2 to 10, the BDTN generates the best thrust vectoring performance under NPR = 4. Above all, the BDTN is well suited to produce vectored thrust for nozzles.

scholarly journals Computational study of Coanda based Fluidic Thrust Vectoring system for optimising Coanda geometry

2016 ◽  
Vol 149 ◽  
pp. 012210 ◽  
Author(s):  
R Bharathwaj ◽  
P Giridharan ◽  
K Karthick ◽  
C Hari Prasath ◽  
K Prakash Marimuthu
Keyword(s):  
Computational Study ◽  
Thrust Vectoring ◽  
Fluidic Thrust Vectoring

scholarly journals Research on control effectiveness of fluidic thrust vectoring

2021 ◽  
Vol 104 (1) ◽  
pp. 003685042199813
Author(s):  
Fei Xue ◽  
Gu Yunsong ◽  
Yuchao Wang ◽  
Han Qin
Keyword(s):  
High Altitude ◽  
Ground State ◽  
Deflection Angle ◽  
Internal Flow ◽  
Lateral Force ◽  
Control Surface ◽  
Low Density ◽  
Thrust Vectoring ◽  
Density State ◽  
Fluidic Thrust Vectoring

In view of the control effects of fluidic thrust vector technology for low-speed aircraft at high altitude/low density and low altitude/high density are studied. The S-A model of FLUENT software is used to simulate the flow field inside and outside the nozzle with variable control surface parameters, and the relationship between the area of control surface and the deflection effect of main flow at different altitudes is obtained. It is found that the fluidic thrust vectoring nozzle can effectively control the internal flow in the ground state and the high altitude/low density state. and the mainstream deflection angle can be continuously adjusted. The maximum deflection angle of the flow in the ground state is 21.86°, and the maximum deviation angle of the 20 km high altitude/low density state is 18.80°. The deflecting of the inner flow of the nozzle is beneficial to provide more lateral force and lateral torque for the aircraft. The high altitude/low density state is taken as an example. When the internal flow deflects 18.80°, the lateral force is 0.32 times the main thrust. For aircraft with high altitude and low density, sufficient lateral and lateral torque can make the flying aircraft more flexible, which can make up the shortcomings of the conventional rudder failure and even replace the conventional rudder surface.

Effect of Control Parameters of Secondary Jet on Fluidic Thrust Vectoring

2014 ◽  
Vol 998-999 ◽  
pp. 613-616
Author(s):  
Li Li ◽  
Dong Ping Wang ◽  
Tsutomu Saito
Keyword(s):  
Flow Field ◽  
Control Parameters ◽  
Jet Injection ◽  
Specific Design ◽  
Initial State ◽  
Thrust Vectoring ◽  
Original Hypothesis ◽  
Fluidic Thrust Vectoring

The flow field was simulated in a 2D convergent-divergent nozzle, for fluidic thrust vectoring with N-S method. Based on the specific design, the effects of control parameters of secondary jet injection is investigated, and a method is proposed to calculate the initial state of secondary jet, which is different from original hypothesis of stagnation. The results showed that the two methods have closed results and the stagnation hypothesis is suitable for the calculation of the initial state of secondary jet.

Lattice-Boltzmann Very Large Eddy Simulations of Fluidic Thrust Vectoring in a Converging/Diverging Nozzle

2020 ◽  
Author(s):  
Avinash Jammalamadaka ◽  
Gregory M. Laskowski ◽  
Yanbing Li ◽  
James Kopriva ◽  
Pradeep Gopalakrishnan ◽  
...  
Keyword(s):  
Lattice Boltzmann ◽  
Large Eddy Simulations ◽  
Thrust Vectoring ◽  
Large Eddy ◽  
Fluidic Thrust Vectoring
Sign in / Sign up

Export Citation Format

Share Document