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CFD computations of NAL experimental airplane with rocket booster using overset unstructured grids
Author(s) -
Togashi Fumiya,
Fujita Takeshi,
Ito Yasushi,
Nakahashi Kazuhiro,
Makino Yoshikazu
Publication year - 2005
Publication title -
international journal for numerical methods in fluids
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.938
H-Index - 112
eISSN - 1097-0363
pISSN - 0271-2091
DOI - 10.1002/fld.940
Subject(s) - airplane , aerodynamics , fuselage , aerospace engineering , booster (rocketry) , unstructured grid , computational fluid dynamics , supersonic speed , mesh generation , grid , computer science , engineering , finite element method , structural engineering , mathematics , geometry
Flows around the NAL jet‐powered experimental airplane with a small rocket booster under the fuselage are computed by solving the Euler equations using the overset unstructured grid method. The main objective of the present study is to evaluate the effect of a small rocket booster, which accelerates the airplane to supersonic speed, on the aerodynamic performance of the airplane during the ascent flight and the booster separation. Two unstructured meshes, one for the airplane and one for the booster, overlap. For the accurate separation simulation, the two bodies are in contact at first, and then the booster mesh is contact mesh is moved relative to the airplane mesh to evaluate flow interactions between two bodies. Copyright © 2005 John Wiley & Sons, Ltd.