Zobrazeno 1 - 10
of 37
pro vyhledávání: '"ISHIGURO, Tomiko"'
Publikováno v:
航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-16. 16:159-164
A numerical procedure to analyze a flowfield through or around a Langley-typed scramjet engine inlet with a strut and an I-shaped thick cowl is proposed. To treat boundary conditions (wall, symmetry etc.) accurately, all boundaries are mapped onto fa
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=jairo_______::a8f6b68d7bb5229c5f3470dc2d3eb1ce
http://id.nii.ac.jp/1696/00043515/
http://id.nii.ac.jp/1696/00043515/
Publikováno v:
航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-16. 16:21-26
The multi-domain technique is used to solve the whole flowfields around the combined configuration of space vehicles. Several computational grids are overlapped with each other in the computational domain, and the solutions are combined by the interp
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=jairo_______::d10bf3b08bbe5a81345da3d596eae9e8
http://id.nii.ac.jp/1696/00043494/
http://id.nii.ac.jp/1696/00043494/
Publikováno v:
航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-14. 14:27-32
Numerical simulations of reacting flowfields in 2/3-dimensional rectangular scramjet combustors with rearward facing steps are presented. They have been carried out by a procedure which was developed to analyze chemically reacting flow with the Harte
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=jairo_______::217831110665846e61bebec60664d18c
http://id.nii.ac.jp/1696/00043431/
http://id.nii.ac.jp/1696/00043431/
Publikováno v:
Technical Report of National Aerospace Laboratory TR-1174T. :29
ラングレー型スクラムジェットエンジン空気取入口の流れ場を解析するための計算手法を提示する。壁や縁のような境界条件を正確に取り扱うために,総ての境界は三つの直方体の表面に
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=jairo_______::4ba9ead812ae4156e8ceccff3814ccf1
http://id.nii.ac.jp/1696/00045414/
http://id.nii.ac.jp/1696/00045414/
Publikováno v:
International Journal for Numerical Methods in Fluids; Aug1989, Vol. 9 Issue 8, p1011-1024, 14p
Publikováno v:
航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-8. 8:19-28
Numerical simulations of flow around shuttle orbiter are performed by solving the 3-dimensional Euler equations. A numerical grid is generated for the whole configuration of shuttle orbiter by using equations of mesh line orthogonality and cell volum
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=jairo_______::97cafafaa6c9e4d7403b8ec4f63c3dad
http://id.nii.ac.jp/1696/00043250/
http://id.nii.ac.jp/1696/00043250/
Publikováno v:
航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-10. 10:279-284
The grid embedding scheme is used to solve the whole flowfields around the combined configuration of Hope, H-II rocket and rocket booster designed by NASDA. Three computational grids are overlapped with each other and the solutions are combined by in
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=jairo_______::88c4abe1678f204e9078cbc7ce67b97b
http://id.nii.ac.jp/1696/00043369/
http://id.nii.ac.jp/1696/00043369/
Publikováno v:
航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-8. 8:211-216
Numerical estimations are performed for our improved TVD schemes (Harten-Yee and Chakravarthy-Osher numerical fluxes) and also for the classical schemes with artifitial dissipation models (Beam-Warming and Obayashi numerical fluxes) through a series
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=jairo_______::a6d5e49575a1d24411572cd85fa5e775
http://id.nii.ac.jp/1696/00043277/
http://id.nii.ac.jp/1696/00043277/
Publikováno v:
航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-10. 10:39-44
Computation of 3-D transonic viscous flows around the ONERA-M6 wing is performed by using several turbulence models with our improved Harten-Yee TVD scheme. The models used here are the Baldwin-Lomax model, Subgrid-Scale (SGS) model and Jones-Launder
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=jairo_______::e7c8d372d1459ffe687c9981ae5f96fc
http://id.nii.ac.jp/1696/00043330/
http://id.nii.ac.jp/1696/00043330/
Publikováno v:
航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-9. 9:121-126
A new difference scheme ATVD2 is proposed, which is constructed by applying the modified flux method proposed by Harten for TVD2 (UNO2) scheme. The numerical experiment of ONERA-M6 wing test case shows the solutions of proposed scheme without artific
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=jairo_______::cd267d683154b2b844c9d1a5f751abaa
http://id.nii.ac.jp/1696/00043303/
http://id.nii.ac.jp/1696/00043303/