Multilevel optimization of a supersonic aircraft

Reduced-order modeling of transonic flows around an airfoil submitted to small deformations

“…On such a domain, airfoil profile modification could be introduced through an additional forcing term in the governing equations, following immersed boundary method [53], for example. A new methodology, originally inspired by 'transpiration' approach for Euler equations [31] and that does not require modification of the governing equations is suggested in the present study, for small shape deformations. This approach relies on the Hadamard formulation [54] of HF model which was previously used in the context of optimal shape design on the basis of Euler equations [55,56].…”

Integration of Multifidelity Multidisciplinary Computer Codes for Design and Analysis of Supersonic Aircraft

“…[1][2][3][4][5][6][7][8][9][10][11][12][13] There are also many examples of conceptual aircraft design reports where the authors described going "deep" in a particular discipline, focusing on a single cruise point low-boom and/or low-drag design in their process. [14][15][16][17][18][19][20][21][22][23][24][25][26][27][28][29][30] Many of these are often byproducts of tool and method development and the testing of optimization algorithms and/or schemes. There are fewer instances focused on supersonic design for low-boom concepts with shape optimization tied to overall vehicle performance.…”

Multilevel functional preconditioning for shape optimisation

“…In contract to this, the proposed volume agglomeration method produces step functions on finer meshes. More precisely, the sequence of spaces generated with the transfers P andP * defined in (12) and (13) does not enjoy enough regularity according the theory of Section 3. This is related to the fact that the orders of accuracy of transfers have a sum equal to 1 + 1 = 2, not strictly larger than 2, see [26].…”

“…In [12], the authors propose a very simplified model for measuring the "sonic boom downwards emission" (SBDE). It consists in evaluating the volume integral of the squared pressure gradient in an "observation box" Ω B (as shown in Figure 3) below the object.…”

“…We end by applying the proposed preconditioner to a pre-industrial shape optimisation loop introduced in [12] and addressing the aerodynamical and sonic boom optimization of supersonic aircraft geometries. We are interested in minimizing a functional j(γ) with respect to a "shape parameter" γ.…”