Experimental aerodynamic assessment and evaluation of an agile highly swept aircraft configuration

Huber, Kerstin Claudie; Schütte, Andreas; Rein, Martin; Löser, Thomas

doi:10.1007/s13272-016-0219-y

Cited by 5 publications

(3 citation statements)

References 16 publications

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“…It was introduced mainly to serve as a common language between the disciplinary analysis tools. Two software libraries [21] called TiXI 6 and TiGL 7 are being developed to ease the use of CPACS. TiXI provides a simple interface to create, read, modify, and write XML datasets such as CPACS.…”

Section: Design Systemmentioning

confidence: 99%

“…A detailed overview of the specific results from the various investigations performed within the DLR project FaUSST, as well as a perspective to its follow-on Mephisto, is provided in a series of articles, presented and published in the DGLR 4 Deutscher Luft-und Raumfahrtkongress in September 2015. While the papers by Huber et al [6], Schütte et al [7], and Paul et al [8] focus on aerodynamics, those by Nauroz [9] and Koch et al [10] are emphasizing on propulsion and air intake aspects. The one by Voß [11] describes design and sizing of a structural model.…”

Section: Introductionmentioning

confidence: 99%

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Multidisciplinary design and aerodynamic assessment of an agile and highly swept aircraft configuration

Liersch

Huber²,

Schütte

et al. 2016

CEAS Aeronaut J

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The characteristics of highly swept aircraft configurations have been studied in a series of consecutive research projects in DLR for more than 15 years. Currently, the investigations focus on the generic SACCON UCAV configuration, which was specified in a common effort together with the NATO STO/AVT-161 task group. This paper is the first one in a series of articles presenting the SACCON-related research work within DLR. First, the article describes the conceptual design studies being performed for this aircraft configuration. At this point the question is raised, whether the simple aerodynamic methods used within conceptual design can be applied to such type of aircraft configurations with sufficient accuracy. Thus, the second part of this article provides a comparison of the aerodynamic characteristics of the SACCON configuration predicted by low-and high-fidelity aerodynamic methods, as well as some results from wind tunnel experiments. Keywords Conceptual aircraft design Á Multi-fidelity Á Highly swept aircraft configurations Á SACCON Á UCAV aerodynamics Abbreviations C A Axial force coefficient [-] C D Drag force coefficient [-] C L Lift force coefficient [-] C N Normal force coefficient [-] C S Body-fixed side force coefficient [-] C Y Side force coefficient [-] C l Rolling moment coefficient [-] C m Pitching moment coefficient [-] C mx Body-fixed X-moment coefficient [-] C my Body-fixed Y-moment coefficient [-] C mz Body-fixed Z-moment coefficient [-] C n Yawing moment coefficient [-] I xx Mass moment of inertia (X-axis) [kg m 2 ] I yy Mass moment of inertia (Y-axis) [kg m 2 ] I zz Mass moment of inertia (Z-axis) [kg m 2 ] V

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Section: Design Systemmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Multidisciplinary design and aerodynamic assessment of an agile and highly swept aircraft configuration

Liersch

Huber²,

Schütte

et al. 2016

CEAS Aeronaut J

View full text Add to dashboard Cite

show abstract

“…predictions of stability and control (S&C) [8,28,[33][34][35][36], design selection, specification, requirements and control ideas [37,38], multidisciplinary design [15,16,18,20], aeroacoustics [39,40], infrared and radar signature [41,42].…”

mentioning

confidence: 99%

Conceptual Design of a Nonconstant Swept Flying Wing Unmanned Combat Aerial Vehicle

Aleisa¹,

Kontis²,

Pirlepeli³

et al. 2023

Journal of Aircraft

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The design of unmanned combat aerial vehicles (UCAVs) is primarily governed by the low-observability requirement for military applications rather than aerodynamic performance. The conceptual design and optimization of UCAV models via size and shape variables for different missions in different flow regimes form a research area for military vehicle design. Flying wing UCAVs experience flow separation during takeoff and landing, and furthermore exhibit stability issues. The aerodynamic performance of these UCAVs can be significantly improved by redesigning their leading-edge sweep angle and wing planform. In the present work, the initial weight determination, aerodynamic sizing, and planform with and without inlet lip integration, and the conceptual design of a nonconstant leading-edge flying wing UCAV configuration are performed. Next, the obtained conceptual design is downscaled 1:20 to be used as a wind-tunnel model and optimized for low-speed conditions using a kriging-based surrogate model with a vortex-lattice method to maximize the lift-to-drag ratio. Later, the optimized design is validated using an open-source computational fluid dynamics code, OpenFOAM 8.0, to verify the accuracy of the surrogate model and to investigate the aerodynamic characteristics. The optimized UCAV design exhibited improved aerodynamic characteristics in terms of the lift-to-drag ratio. Furthermore, the aerodynamic performance and flowfield of the optimized UCAV model with and without inlet lip integration have been evaluated at low and high speeds.

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Assessment of body-freedom flutter for an unmanned aerial vehicle

et al. 2018

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Experimental aerodynamic assessment and evaluation of an agile highly swept aircraft configuration

Cited by 5 publications

References 16 publications

Multidisciplinary design and aerodynamic assessment of an agile and highly swept aircraft configuration

Multidisciplinary design and aerodynamic assessment of an agile and highly swept aircraft configuration

Conceptual Design of a Nonconstant Swept Flying Wing Unmanned Combat Aerial Vehicle

Assessment of body-freedom flutter for an unmanned aerial vehicle

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