This paper presents the development of a fully implicit, low-memory discrete-adjoint method by means of automatic source-code differentiation applied to the Helicopter Multi-Block computational fluid dynamics solver. The method is suitable for applications in flight mechanics, as well as shape optimization, and is demonstrated in this paper for popular flow cases reported in the literature. In particular, adjoint computational fluid dynamics computations were undertaken for airfoils, wings, and rotor-blade cases, and the obtained results were found to agree well with published solutions and with finite differences of flow derivatives. The method has been demonstrated for inviscid and viscous cases, and the results suggest that the current implementation is robust and efficient. The cost of the adjoint computations is relatively low due to the employed source-code differentiation, and most of the time, it is no more than the cost of a steady-state flow solution.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Fully Implicit Discrete-Adjoint Methods for Rotorcraft Applications


    Contributors:

    Published in:

    AIAA Journal ; 54 , 2 ; 735-749


    Publication date :

    2015-12-15


    Size :

    15 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





    Fully Implicit Discrete Adjoint Methods for Rotorcraft Applications (AIAA 2015-1491)

    Biava, Massimo / Barakos, George N. | British Library Conference Proceedings | 2015


    Fully Implicit Discrete Adjoint Methods

    Biava, Massimo / Woodgate, Mark / Barakos, George N. | AIAA | 2015