ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Dynamic drag reduction mechanism of self-aligned aerodisks on hypersonic aircraft
Received date: 2021-11-08
Revised date: 2022-04-15
Accepted date: 2022-05-06
Online published: 2022-05-09
Supported by
National Key Project(GJXM92579)
To address the drag reduction problem of hypersonic aircraft during dynamic maneuver， the dynamic drag reduction effects of self-aligned aerodisks are studied based on the unsteady flow/kinematics coupled method and dynamic hybrid grid generation technique. Drag characteristics of aircraft are also analyzed with variation of different parameters to provide reference for hypersonic aircraft design and optimization. In addition， differences in dynamic drag reduction mechanisms between the fixed and self-aligned aerodisks are discussed. The numerical results show that self-aligned aerodisks， always aligning with the incoming flow， are helpful to maintain the structure of recirculation zone during maneuvering. Moreover， self-aligned aerodisks are able to reconstruct the flow field even at a high angle of attack. Compared to that of fixed aerodisks， the drag reduction effect of self-aligned aerodisks can be largely improved in more than 80% of the oscillation period. Furthermore， the superiority of the self-aligned method clearly increases with the growing pitch angle.
Rong HAN , Wei LIU , Xiaoliang YANG . Dynamic drag reduction mechanism of self-aligned aerodisks on hypersonic aircraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023 , 44(4) : 126633 -126633 . DOI: 10.7527/S1000-6893.2022.26633
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