JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
titleエンジンインテーク統合時における超音速最適翼型の平面形依存性に関する調査
Other TitleInvestigation of Planform Dependency of Optimum Supersonic Airfoil with Integrated Engine Intake
Author(jpn)岸, 祐希; 北崎, 慎哉; Ariyarit, Atthaphone; 牧野, 好和; 金崎, 雅博
Author(eng)Kishi, Yuki; Kitazaki, Shinya; Ariyarit, Atthaphone; Makino, Yoshikazu; Kanazaki, Masahiro
Author Affiliation(jpn)首都大学東京; 首都大学東京; 首都大学東京; 宇宙航空研究開発機構(JAXA); 首都大学東京
Author Affiliation(eng)Tokyo Metropolitan University; Tokyo Metropolitan University; Tokyo Metropolitan University; Japan Aerospace Exploration Agency (JAXA); Tokyo Metropolitan University
Issue Date2016-12-27
Publisher宇宙航空研究開発機構(JAXA)
Japan Aerospace Exploration Agency (JAXA)
Publication title宇宙航空研究開発機構特別資料: 第48回流体力学講演会/第34回航空宇宙数値シミュレーション技術シンポジウム論文集
JAXA Special Publication: Proceedings of the 48th Fluid Dynamics Conference / the 34th Aerospace Numerical Simulation Symposium
VolumeJAXA-SP-16-007
Start page85
End page90
Publication date2016-12-27
Languagejpn
eng
AbstractIn this research, the supersonic wing design problem for SST with integrated engine intake and nacelle is discussed to obtain design knowledge of the supersonic airfoil in view of wing planform dependency in realistic configuration. Two planforms were considered ― a quadruple tapered wing with a high sweep-back angle and a single tapered wing with a low sweep-back angle. To reduce the computational time, the design problems were solved by a multi-fidelity design method, which is the evolutionary computation based exploration using the hybrid surrogate models based on two different physical fidelity results. The hybrid surrogate model which was combined Kriging model with radial basis function (RBF) makes optimizations more efficiently than Kriging model. To evaluate the aerodynamic performance, the compressive Euler equation and the linearized compressive potential equation were employed as two different fidelity solvers. Through optimum designs, two kinds of design knowledge are obtained. Firstly, in airfoil design, the shape of the forward camber and twisted angle have the largest effect on drag reduction. In case of low sweep-back wing, an airfoil which has small positive camber and small twisted down angle has found to be optimum. On the other hands, In case of low sweep-back wing, an airfoil which has a negative camber at the leading edge or higher twisted down angle compared to low swept-back wing’s one has shown to be optimum. Secondly, the way of aerodynamic interference between wing, engine, and fuselage depends on planforms.
Description会議情報: 第48回流体力学講演会/第34回航空宇宙数値シミュレーション技術シンポジウム (2016年7月6日-8日. 金沢歌劇座), 金沢市, 石川
形態: カラー図版あり
Meeting Information: 48th Fluid Dynamics Conference /the 34th Aerospace Numerical Simulation Symposium (July 6-8, 2016. The Kanazawa Theatre), Kanazawa, Ishikawa, Japan
Physical characteristics: Original contains color illustrations
Document TypeConference Paper
JAXA Category特別資料
NASA Subject CategoryFluid Mechanics and Thermodynamics
ISSN1349-113X
NCIDAA11984031
SHI-NOAA1630031008
Report NoJAXA-SP-16-007
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/577431


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