Proceedings ArticleDOI
High speed test results of subsonic, turbofan scarf inlets
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The article was published on 1993-06-28. It has received 13 citations till now. The article focuses on the topics: Turbofan.read more
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Journal ArticleDOI
Multi-objective optimisation of short nacelles for high bypass ratio engines
TL;DR: The multi-objective optimisation approach using an evolutionary genetic algorithm for the design of new aero-engine nacelles was successfully demonstrated for the new nacelle design challenge and the overall system was shown to enable the identification of the viable nacelles design space.
Patent
Biplanar scarfed nacelle inlet
TL;DR: In this paper, a scarfed nacelle inlet for channelling aiflow to an engine having a longitudinal center line axis (ENGINE C/L) is described.
Patent
Air inlet for commercial aircraft jet engine nacelle
TL;DR: An air inlet is of a scarf type and the internal profile of the upper sections of its lip includes, with respect to the identical and symmetrical horizontal sections of the lip, an internal bulge that is bigger for a larger scarf angle.
Journal ArticleDOI
Non-axisymmetric aero-engine nacelle design by surrogate-based methods
TL;DR: In this article, the authors present an approach for the design and optimisation of 3D drooped and scarfed non-axisymmetric nacelles based on surrogate-based adapted methods.
Proceedings ArticleDOI
Computational Study of the Aerodynamic Performance of Three-Dimensional Subsonic Inlets
John M. Abbott,John W. Slater +1 more
TL;DR: In this paper, a computational study has been conducted to assess the aerodynamic performance of 3D subsonic inlets using the WIND 3D Navier-Stokes CFD code.
References
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Proceedings ArticleDOI
Aerodynamic performance of scarf inlets
TL;DR: In this article, a wind tunnel test program is presented which illustrates the aerodynamic performance of two different scarf inlet designs and summarizes the advantages and limitations of a scarf-inlet compared to an axisymmetric inlet.
Proceedings ArticleDOI
Aeroacoustic performance of a scoop inlet
TL;DR: In this paper, a low speed wind tunnel test demonstrated the aerodynamic and acoustic performance of a scoop inlet and demonstrated that higher velocities on the lower lip result in a higher attainable angle of attack before internal flow separation.