Variable-complexity aerodynamic optimization of an HSCT wing using structural wing-weight equationsA new approach for combining conceptual and preliminary design techniques for wing optimization is presented for the high-speed civil transport (HSCT). A wing-shape parametrization procedure is developed which allows the linking of planform and airfoil design variables. Variable-complexity design strategies are used to combine conceptual and preliminary-design approaches, both to preserve interdisciplinary design influences and to reduce computational expense. In the study, conceptual-design-level algebraic equations are used to estimate aircraft weight, supersonic wave drag, friction drag and drag due to lift. The drag due to lift and wave drag are also evaluated using more detailed, preliminary-design-level techniques. The methodology is applied to the minimization of the gross weight of an HSCT that flies at Mach 3.0 with a range of 6500 miles.
Document ID
19920043061
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hutchison, M. G. (NASA Langley Research Center Hampton, VA, United States)
Unger, E. R. (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 Institute and State University Blacksburg, United States)