High fidelity and high efficiency method for sonic boom predictions in supersonic flights
US10146903B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Nov 11, 2015 |
| Grant date | Dec 4, 2018 |
| Priority date | — |
| Expiry date | Feb 3, 2037 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG06F2119/10
- WIPO fieldComputer technology
- WIPO sectorElectrical engineering
Abstract
A computer-implemented sonic boom prediction method for use in designing a supersonic aircraft is disclosed herein. The method includes receiving physical parameters and performance parameters for a supersonic aircraft, generating a three-dimensional (3D) flow field around the supersonic aircraft for at least one airspeed using a CFD model in a first region of a near field bounded by a first radial distance and a propagation model in a second region of the near field bounded by the first radial distance and the second radial distance. The 3D flow field generated by the CFD model is used as a boundary condition for the propagation model. The method further includes estimating sonic boom signatures on a ground surface using a long distance sonic boom propagation model that incorporates the 3D flow field estimated by the propagation model as an initial condition. The parameters are adjusted to reduce estimated sonic boom signatures.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.