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The viscous optimal shape design, via spectral solutions
Author(s) -
Nastase Adriana
Publication year - 1999
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/(sici)1097-0363(19990530)30:2<137::aid-fld825>3.0.co;2-u
Subject(s) - fuselage , drag , swept wing , supersonic speed , computation , camber (aerodynamics) , computational fluid dynamics , drag divergence mach number , aerodynamics , airfoil , delta wing , mach number , lift induced drag , drag coefficient , geometry , mathematics , mechanics , aerospace engineering , engineering , physics , algorithm
The shape of a flying configuration is globally optimized if its camber, twist, thickness and the similarity parameters of its planform are determined in order to obtain a minimum drag at cruising Mach number. The optimum–optimorum (OO) theory of the author solves this problem by using a lower limit hyper‐surface for the drag functional. A multipoint design is realized by using movable leading edge flaps. The iterative OO theory is used for the computation of the friction drag, for the determination of the viscosity effect in the optimal shape of the flying configuration and to perform the multidisciplinary design by including structure and thermal auxiliary conditions. A proposal of a fully‐optimized shape of supersonic transport aircraft with twin integrated fuselages is also made. Copyright © 1999 John Wiley & Sons, Ltd.