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Autor: Azuma, Daisuke, Nakamura, Yoshiaki

Publikováno v: 航空宇宙技術研究所特別資料: 航空宇宙数値シミュレーション技術シンポジウム2001論文集 = Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2001. 53:263-266

The low-speed flow for a 45 deg sweep delta wing is numerically simulated to see the effects of leading-edge rotation on aerodynamic forces. In the present study, cylindrical leading edges are employed, where the portion from x = 0.25 C to C can be r

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::1a501679cc93a1ce67b336d6f6467378
http://id.nii.ac.jp/1696/00038075/

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Numerical analysis of supersonic transport's leading-edge vortex flaps

Autor: Higaki, Kyoko, Maekawa, Shoji

Publikováno v: 航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory. 37:63-68

航空宇宙技術研究所 12-13 Jun. 1997 東京日本
National Aerospace Laboratory 12-13 Jun. 1997 Tokyo Japan
前縁ボルテックスフラップは、フラップ上に前縁渦を形成することにより翼の揚抗比を改善�

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::6c425151c70d38c405c58fa1416a7f94
http://id.nii.ac.jp/1696/00037130/

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Detailed flow field around a leading-edge slat at low Reynolds numbers

Autor: Makiya, Sanehiro, Inasawa, Ayumu, Asai, Masahito

Publikováno v: 宇宙航空研究開発機構特別資料: 境界層遷移の解明と制御研究会講演論文集第40回 = JAXA Special Publication: Proceedings of the 40th JAXA Workshop on Investigation and Control of Boundary-Layer Transition. :27-30

Flows around a leading-edge slat are investigated experimentally at Reynolds numbers Re less than or equal to 5.2 x 10(exp 5). When the slat operates to suppress the leading-edge stall, a periodic vortex shedding occurs due to the instability of lami

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::3f73c312c9f8307dcd7f00f707fa7f32
http://id.nii.ac.jp/1696/00005524/

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CFD analysis of JAXA high-lift configuration model using overset mesh

Autor: Nagata, Taku, Ochi, Akio, Shima, Eiji

Publikováno v: 宇宙航空研究開発機構特別資料: 第39回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2007論文集 = JAXA Special Publication: Proceedings of 39th Fluid Dynamics Conference/Aerospace Numerical Simulation Symposium 2007. :190-195

Flow around JAXA HLD (High Lift Devices) wind tunnel model is analyzed by RANS (Reynolds Averaged Navier Stokes) CFD (Computational Fluid Dynamics) method and compared with the experimental data obtained by JAXA. Unstructured mesh with overset techni

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::b95eee11d5f39bc5d2130b2b60bc7a07
http://id.nii.ac.jp/1696/00005631/

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横流れを考慮した高揚力翼型展開形態の設計探査

Autor: Jeong, Shinkyu, Kanazaki, Masahiro, Imamura, Taro, Yamamoto, Kazuomi

In this paper, a multi-objective design exploration for a three-element airfoil which consists of a slat, main wing, and flap was carried out by paying attention to the span wise flow effect. Reynolds Averaged Navier-Stokes Solver (RANS) was used for

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::40168f4e73cab55c86a5c4a5e24fb981
http://id.nii.ac.jp/1696/00005612/

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圧縮揚力による超音速デルタ翼の揚抗比増加に関する数値解析

Autor: Kanamori, Masashi, Imamura, Osamu, Suzuki, Kojiro

We numerically analyze supersonic flows around a delta wing with bent wing tip. The results show that the lift and drag forces decrease with the increase in the bending angle. But the local augmentation is observed around the hinge line of bending in

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::2aec49c7125e833af4b15e396c3cceaf
http://id.nii.ac.jp/1696/00005603/

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Flow simulation around JAXA high-lift configuration model using high-order unstructured method

Autor: Haga, Takanori, Onishi, Naofumi, Sawada, Keisuke, Masunaga, Akihisa, Uchiyama, Naoki

An aerodynamics simulation code using high-order Spectral Volume (SV) method has been developed, and flow simulations around JAXA high-lift configuration model were conducted on the Earth Simulator. The obtained results of the Euler computation are c

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::c972c53de6e1c401dd42aff21c9b3280
http://id.nii.ac.jp/1696/00005632/

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Numerical calculation of flow around the unsteady flapping wing

Autor: Liu, Hao, Inada, Yoshinobu, Aoyama, Takashi, Aono, Hikaru

Aerodynamics around unsteady flapping wings is analyzed by using CFD (Computational Fluid Dynamics) techniques. Two types of flapping wing are modeled and analyzed referring to the hovering motion of hawkmoth and honeybee. Multi-block technique is us

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::31323cd640337076de1629ac2c2cdb7e
http://id.nii.ac.jp/1696/00005622/

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Aerodynamic shape optimization for supersonic aircraft configurations

Autor: Reuther, J., Alonso, J. J., Rimlinger, M. J., Jameson, A.

Publikováno v: 宇宙航空研究開発機構特別資料 = JAXA Special Publication: Proceedings of International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport (SST-CFD Workshop). :109-123

SST-CFD Workshop. International CFD Workshops for Super-sonic Transport Design 航空宇宙技術研究所 19980316-19980317 東京日本
SST-CFD Workshop. International CFD Workshops for Super-sonic Transport Design National Aerospace Laborato

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::4a025d3a353541c03c281b8b435dc553
http://id.nii.ac.jp/1696/00005740/

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