The sonic boom intensity is predicted by the wave form parameter method, which is validated by PCBoom. The drag coefficient is corrected by the Harris wave drag calculation and form factor method. PANAIR is integrated to perform automated aerodynamic analysis. The Mach plane cross-sectional area is calculated based on the parametric geometry model. Methodologies appropriate to SSBJs are developed in the GENUS environment.

SSBJs are regarded as the pioneers of the next generation of supersonic airliners. This paper discusses the application of this environment to the design of supersonic business jets (SSBJs). The GENUS aircraft design environment's key features are that it is modular, expandable, flexible, independent, and sustainable. This paper introduces a multidisciplinary design analysis and optimization environment called GENUS. Based on the analysis, low-boom and low-drag design principles are identified. In this research, using the methods described and publically available data on the concepts, the supersonic drag elements and sonic boom signature due to volume distribution and lift distribution are analysed. The propagation method for the near-field signature in a stratified windy atmosphere is the waveform parameter method. The F-function is decomposed to the F-function due to volume and the F-function due to lift to investigate the separate effect on sonic boom. For sonic boom prediction, the near-field pressure is predicted through the Whitham F-function method. The drag coefficient is corrected by the Harris wave drag formula and form factor method. The panel method PANAIR is integrated to perform automated aerodynamic analysis. The aerodynamic analysis and sonic boom prediction are investigated by a number of conceptual-level numerical approaches. This paper evaluates six supersonic business jet (SSBJ) concepts in a multidisciplinary design analysis optimisation (MDAO) environment in terms of their aerodynamics and sonic boom intensities. Furthermore, correctly positioned wingtips may also be used to smooth the undertrack signature, reducing the sonic boom. The results show the tradeoff between planform shapes that efficiently use compression lift to increase the lift-to-drag ratio and a smooth undertrack pressure signature to reduce ground-level noise.

Genetic and local optimizers are used to search the Kriging surrogates. The effects of parameterizing the planform of a baseline model (NASA’s 69 deg wing–body) with 6- and 11-variables are explored. The use of effective nondominated sampling is used to further improve the solutions found. The use of Kriging-based surrogate models, coupled with expected hypervolume improvement in a Kriging believer framework, allows efficient global optimization of the selected wing design parameters. Although, there are challenges to balance the volume with packaging and control requirements, these concepts prove the feasibility of low-boom low-drag design for supersonic transports from a multidisciplinary perspective.Ī surrogate-assisted methodology to accelerate the design space exploration process and multi-objective optimization of a notional low-drag, low-boom supersonic transport planform using Euler computational fluid dynamics with an empirical parasite drag addition and an augmented Burgers equation solver is demonstrated. A family of different classes of supersonic aircraft, including a single-seat supersonic demonstrator (0.47 psf), a 10-passenger supersonic business jet (0.90 psf) and a 50-seat supersonic airliner (1.02 psf), are designed to demonstrate the sonic boom stealth design principles. The sonic boom stealth concept is expected to inspire the supersonic aircraft designers to design low-boom concepts through aircraft shaping and to achieve low ground impacts. A new inspiring design concept-sonic boom stealth is proposed by the authors. With this model, the authors reveal the relationship between the sonic boom signature and the lift and volume distributions and the possibility to optimise the lift distribution and volume distribution together so that they can cancel each other at some region. A conceptual design model appropriate to supersonic transports with low-to-medium-fidelity methods are developed in GENUS. This paper introduces a supersonic transport aircraft design model developed in the GENUS aircraft conceptual design environment.

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