Löchert, Patrick und Huber, Kerstin Claudie und Ghoreyshi, Mehdi und Allen, Jacob (2019) Control device effectiveness studies of a 53° swept flying wing configuration. Experimental, computational, and modeling considerations. Aerospace Science and Technology, 93 (105319), Seiten 1-24. Elsevier. doi: 10.1016/j.ast.2019.105319. ISSN 1270-9638.
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Offizielle URL: https://doi.org/10.1016/j.ast.2019.105319
Kurzfassung
The present investigation covers studies of different control devices on several 53° swept flying wing configurations without a vertical tail plane. The planform, developed under the NATO AVT-251 Task Group, is referred to as the MULDICON (or MULti-DIsciplinary CONfiguration). The objectives of this article are twofold: (1) to design yaw control surfaces for the MULDICON wing using an experimental/computational approach and (2) to develop aerodynamic models that rapidly and accurately predict the effectiveness of control surfaces over a wide range of flight conditions. The yaw control surface design (position and size) should provide sufficient yaw moment with almost no contribution in roll and pitch moment. To identify such concepts, a number of preliminary experiments on a generic flying wing configuration have been conducted. Two promising concepts from wind tunnel tests were then numerically examined for being implemented in the MULDICON baseline wing. Concepts with spoilers and a split flap were specifically considered. For medium to high angles of attack, the flow topology of the baseline wing is dominated by a vortical flow field on the upper outer wing. This leads to interactions between vortex and the control device which influences the flow and the attitude of the control device on the upper wing side. Furthermore, this work considers developing aerodynamic models for predicting stability derivatives of several MULDICON designs over a wide range of flight conditions. Aerodynamic loads models are only developed for normal force and pitch moment coefficients, however, the developed approach can easily being extended to include lateral aerodynamic coefficients as well. Quasi-steady models of this work are power series expansions of traditional linear aerodynamic models to capture nonlinear effects. Additionally, the models can estimate static and dynamic stability derivatives and the control surface powers.
elib-URL des Eintrags: | https://elib.dlr.de/128954/ | ||||||||||||||||||||
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Dokumentart: | Zeitschriftenbeitrag | ||||||||||||||||||||
Titel: | Control device effectiveness studies of a 53° swept flying wing configuration. Experimental, computational, and modeling considerations | ||||||||||||||||||||
Autoren: |
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Datum: | 31 Juli 2019 | ||||||||||||||||||||
Erschienen in: | Aerospace Science and Technology | ||||||||||||||||||||
Referierte Publikation: | Ja | ||||||||||||||||||||
Open Access: | Ja | ||||||||||||||||||||
Gold Open Access: | Nein | ||||||||||||||||||||
In SCOPUS: | Ja | ||||||||||||||||||||
In ISI Web of Science: | Ja | ||||||||||||||||||||
Band: | 93 | ||||||||||||||||||||
DOI: | 10.1016/j.ast.2019.105319 | ||||||||||||||||||||
Seitenbereich: | Seiten 1-24 | ||||||||||||||||||||
Herausgeber: |
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Verlag: | Elsevier | ||||||||||||||||||||
Name der Reihe: | Design of a UCAV Concept | ||||||||||||||||||||
ISSN: | 1270-9638 | ||||||||||||||||||||
Status: | veröffentlicht | ||||||||||||||||||||
Stichwörter: | CFD; Stability and control; Tailless flying wing; Vortex dominated flow; System identification; Training maneuver | ||||||||||||||||||||
HGF - Forschungsbereich: | Luftfahrt, Raumfahrt und Verkehr | ||||||||||||||||||||
HGF - Programm: | Luftfahrt | ||||||||||||||||||||
HGF - Programmthema: | Flugzeuge | ||||||||||||||||||||
DLR - Schwerpunkt: | Luftfahrt | ||||||||||||||||||||
DLR - Forschungsgebiet: | L AR - Aircraft Research | ||||||||||||||||||||
DLR - Teilgebiet (Projekt, Vorhaben): | L - Militärische Technologien (alt) | ||||||||||||||||||||
Standort: | Braunschweig | ||||||||||||||||||||
Institute & Einrichtungen: | Institut für Aerodynamik und Strömungstechnik | ||||||||||||||||||||
Hinterlegt von: | Löchert, Patrick | ||||||||||||||||||||
Hinterlegt am: | 02 Sep 2019 11:31 | ||||||||||||||||||||
Letzte Änderung: | 31 Okt 2023 14:03 |
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