Abstract
An inverse design of supersonic aircraft with low-boom in full-carpet, low-drag, and longitudinal trim using cylindrical pressure distribution is proposed. Defining consistent cylindrical pressure distribution and reconstructing geometry from the cylindrical pressure distribution have been challenging. In this paper, a function to express consistent cylindrical pressure distribution that satisfies the Helgason–Ludwig consistency conditions is used to define a target. Projections onto convex sets that are used in the field of limited angle tomography are applied to reconstruct a geometry iteratively. For sonic boom propagation, a fast low-fidelity method with Cole–Hopf transformation to solve the Burgers equation is proposed. An implementation of multipole analysis with piecewise series expansion of the multipole function is included and is used for resolving circumferential flow effects in near-field analysis for sonic boom propagation and for comparison with far-field linear theory. Case studies show the validity of the proposed methods.
Published Version
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