Automated Optimisation of the MULDICON Inlet with Minimum Losses and Reduced Sight onto the Compressor Front Face

Voß, C.; Becker, Richard-Gregor; Trost, Marco

doi:10.2514/6.2018-3165

Cited by 2 publications

(2 citation statements)

References 11 publications

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“…Due to limitations in time and resources, their final results could not be incorporated directly into the overall aircraft concept; however, their demands were considered as boundary conditions where possible. More Details on engine integration work for MULDICON can be found in [51][52][53][54].…”

Section: Muldicon Designmentioning

confidence: 99%

Design studies and multi-disciplinary assessment of agile and highly swept flying wing configurations

Liersch¹,

Schütte²,

Siggel

et al. 2020

CEAS Aeronaut J

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This article belongs to a series of publications on the design and assessment of the MULDICON UCAV configuration. MULDICON is a 53° swept flying wing combat aircraft concept, investigated in a common effort between the DLR research project Mephisto and the NATO STO Research Task Group AVT-251. This article focuses on the development of the overall concept starting from its predecessor, the SACCON configuration, and the requirements which had been defined for the MULDICON design task. A second focus is placed on the investigation of the vortex-dominated flow topology arising around such a configuration and its sensitivity to specific geometric changes. Furthermore, the article briefly introduces the DLR conceptual aircraft design system and the extensions which have been developed for improving its capabilities for UCAV assessment. Finally, an industrial view on the MULDICON design task is provided, as well as a conclusion of the Mephisto results and an outlook upon further work.

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Section: Muldicon Designmentioning

confidence: 99%

Design studies and multi-disciplinary assessment of agile and highly swept flying wing configurations

Liersch¹,

Schütte²,

Siggel

et al. 2020

CEAS Aeronaut J

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“…Optimization method, which can significantly improve the inlet aerodynamic performances, has attracted more and more interest recently. [15][16][17][18][19][20][21] In general, the inlet geometrical parameters are employed as design variables and optimization algorithms are performed to obtain optimal inlet configurations. [20][21][22] From the preceding literature survey, the considered optimization objectives were usually inlet mass flow, total pressure recovery, flow uniformity, and so on, but the starting ability was basically not studied.…”

Section: Introductionmentioning

confidence: 99%

Parameterization and optimization design of a two-dimensional axisymmetric hypersonic inlet

Shi

Wang

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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Optimization method, as a promising way to improve inlet aerodynamic performance, has received increasing attention. The present research is undertaken to design a two-dimensional axisymmetric hypersonic inlet using parametric optimization. The inlet configuration is parameterized and optimized in consideration of total pressure recovery and starting performance. A Pareto front is obtained by solving the multi-objective optimization problem. Then, the flow structures of the optimized inlets are analyzed and the starting performances are evaluated. Results show that the total pressure loss mainly occurs in the internal contraction section, especially near the inlet entrance, and therefore the total pressure recovery coefficient can be greatly improved by decreasing external compression. As a result, the guidance for designing high-performance inlets is concluded. Besides, it is found that as the internal contraction ratio increases, the inlet starting ability becomes worse, which attributes to the larger separation bubble at the inlet entrance. Finally, the total pressure recovery coefficient and the starting Mach number of the optimized inlets are obtained, which can be a reference for engineering design.

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Automated Optimisation of the MULDICON Inlet with Minimum Losses and Reduced Sight onto the Compressor Front Face

Cited by 2 publications

References 11 publications

Design studies and multi-disciplinary assessment of agile and highly swept flying wing configurations

Design studies and multi-disciplinary assessment of agile and highly swept flying wing configurations

Parameterization and optimization design of a two-dimensional axisymmetric hypersonic inlet

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