Abstract This chapter presents a method for computing rotorcraft stability derivatives based on the discrete adjoint method. The adjoint equations are derived by means of automatic source-code differentiation, and solved using a fully implicit, low-memory fixed-point iteration scheme. The method is demonstrated for two rotor-blade cases, and the obtained results were found to agree well with finite differences of flow derivatives. 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.


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    Title :

    Computation of Rotorcraft Stability Derivatives Using the Discrete Adjoint Method


    Contributors:
    Biava, M. (author) / Barakos, G. (author)


    Publication date :

    2017-01-01


    Size :

    20 pages




    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English





    Fully Implicit Discrete-Adjoint Methods for Rotorcraft Applications

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



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

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