A 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 files at Mach 3.0 with a range of 6500 miles.
Variable-complexity aerodynamic optimization of an HSCT wing using structural wing-weight equations
Variable-komplexe aerodynamische Optimierung des Flügels eines Hochgeschwindigkeits-Transportflugzeuges mittels struktureller Tragflügel-Gewicht-Gleichungen
AIAA-Papers ; 1-18
1992
18 Seiten, 21 Bilder, 5 Tabellen, 27 Quellen
Aufsatz (Konferenz)
Englisch
LUFTFAHRTTECHNIK , TRANSPORTFLUGZEUG , HOCHGESCHWINDIGKEIT , KONSTRUKTION , AUFBAU (FAHRZEUG) , ENTWURFSPARAMETER , TRAGFLUEGELUMSTROEMUNG , PROFILSTROEMUNG , GEWICHTUNGSFUNKTION , MECHANISCHER WELLENWIDERSTAND , REIBUNGSWIDERSTAND , UEBERSCHALLSTROEMUNG , EXPERIMENTELLE UNTERSUCHUNG , FORSCHUNGSBERICHT