Aerodynamic optimization of an HSCT configuration using variable-complexity modelingAn approach to aerodynamic configuration optimization is presented for the high-speed civil transport (HSCT). A method to parameterize the wing shape, fuselage shape and nacelle placement is described. Variable-complexity design strategies are used to combine conceptual and preliminary-level design approaches, both to preserve interdisciplinary design influences and to reduce computational expense. Conceptual-design-level (approximate) methods are used to estimate aircraft weight, supersonic wave drag and drag due to lift, and landing angle of attack. The drag due to lift, wave drag and landing angle of attack are also evaluated using more detailed, preliminary-design-level techniques. New, approximate methods for estimating supersonic wave drag and drag due to lift are described. The methodology is applied to the minimization of the gross weight of an HSCT that flies at Mach 2.4 with a range of 5500 n.mi. Results are presented for wing planform shape optimization and for combined wing and fuselage optimization with nacelle placement. Case studies include both all-metal wings and advanced composite wings.
Document ID
19930035809
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hutchison, M. G. (NASA Langley Research Center Hampton, VA, United States)
Mason, W. H. (NASA Langley Research Center Hampton, VA, United States)
Grossman, B. (NASA Langley Research Center Hampton, VA, United States)
Haftka, R. T. (Virginia Polytechnic Inst. and State Univ. Blacksburg, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1993
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 93-0101
Meeting Information
Meeting: AIAA, Aerospace Sciences Meeting and Exhibit