This paper investigates a morphing hypersonic waverider concept and determines the morphing surface accuracy and control requirements required to achieve Mach 5 to Mach 3.5 on-design operation. Hypersonic waveriders are of interest in the aerospace community due to their significant aerodynamic performance improvements over conventional vehicles in the hypersonic flight regime, although designed for only a single, specific Mach number. The Naval Research Laboratory (NRL) morphing waverider achieves on-design waverider performance across a range of speeds by maintaining shock attachment through morphing the waverider’s lower stream surface and maintaining a rigid leading edge and top surface. A Q-DEIM sensitivity analysis is performed to define a set of actuator locations on the lower surface, which ensures that the morphing error, defined by the difference between the morphed surface and the desired surface shape, is minimized. This paper demonstrates 5- and 14-control-point cases that reduce 87% and 95% of the morphing error, respectively, for a 2-in.-wide morphing hypersonic waverider designed for wind tunnel testing across Mach numbers ranging from Mach 5 to Mach 3.5. Viscous computational fluid dynamics is used to determine the calculated morphing-error effect on the resulting aerodynamics. The results demonstrate that the 14- and 5-control-point cases achieve 97% and 95% of the performance benefits relative to the on-design waverider stream surface.


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    Title :

    Mach 5–3.5 Morphing Waverider Accuracy and Aerodynamic Performance Evaluation


    Contributors:

    Published in:

    Journal of Aircraft ; 56 , 5 ; 2047-2061


    Publication date :

    2019-08-23


    Size :

    15 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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