Interest in low-observable aircraft and in lowering an aircraft's exhaust system weight sparked decades of research for fixed geometry exhaust nozzles. The desire for such integrated exhaust nozzles was the catalyst for new fluidic control techniques; including throat area control, expansion control, and thrust-vector angle control. This paper summarizes a variety of fluidic thrust vectoring concepts that have been tested both experimentally and computationally at NASA Langley Research Center. The nozzle concepts are divided into three categories according to the method used for fluidic thrust vectoring: the shock vector control method, the throat shifting method, and the counterflow method. This paper explains the thrust vectoring mechanism for each fluidic method, provides examples of configurations tested for each method, and discusses the advantages and disadvantages of each method.
Summary of Fluidic Thrust Vectoring Research Conducted at NASA Langley Research Center
21st AIAA Applied Aerodynamics Conference ; 2003 ; Orlando, FL, United States
2003-01-01
Conference paper
No indication
English
AIAA-2003-3800 Summary of Fluidic Thrust Vectoring Research at NASA Langley Research Center
British Library Conference Proceedings | 2003
|NTRS
|NTRS | 2008
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