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.


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    Title :

    Summary of Fluidic Thrust Vectoring Research Conducted at NASA Langley Research Center


    Contributors:

    Conference:

    21st AIAA Applied Aerodynamics Conference ; 2003 ; Orlando, FL, United States


    Publication date :

    2003-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





    AIAA-2003-3800 Summary of Fluidic Thrust Vectoring Research at NASA Langley Research Center

    Deere, K. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2003




    NASA Langley Research Center

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