| Popis: |
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. |
