Lifting Surface Design Using Multidisciplinary OptimizationThis thesis develops a method for optimal planform design of wings and wing-tail configurations that improves the designs using nonlinear optimization while accounting for induced, profile, and compressibility drag, bending and buckling weight, section maximum lift constraints, and static aeroelasticity. |
Common terms and phrases
active constraints aerodynamic aeroelasticity aileron aircraft airfoil algorithm analysis angle of attack baseline calculated chord climb Clmaz compressibility drag constraint gradients cosē cruise design endload design loads design variables estimate evaluated Figure fixed fuel fraction fuselage gear constraints gear placement constraint geometry Hessian Hessian matrix improvement induced camber induced drag internal iteration Lagrange multipliers leading edge Lift coefficient distributions lifting surface design line search load factor Mach number mact matrix maximum lift constraints maximum section lift merit function method mistrim MTOW optimal design optimized wing-tail optimizer-directed iteration parameters parasite drag pitching pitching moment planform pressure problem quadratic programming reduced rib and stringer rib spacing satisfy Section Lift Coefficient sequential quadratic programming shear center sheared wing skin thickness span spanload Spanwise Coordinate ft stall speed static margin step stringer spacing sweep and dihedral swept wing trim vector vortex wing design wing fuel wing optimization wing tips wing weight wing-tail configurations