In this paper we present a successive derivation of basic equations in order to enlighten the implicit relationships between some of the most common objective functions employed in aircraft conceptual design. Correlation between financial and technical figures of merit rely on some important assumptions that may break and therefore it is unadvised to look for financially optimal designs using technical objective functions. As shown in the results section, relationships between technical-only figures of merit hold and its behavior is even mathematically predictable. On the other hand, technical-financial relationships depend on market variables (price and market forecast, mainly) that can only be captured by proper financial models. In the results section it is shown how optimization using technicalonly objective functions overlook important economical trades and thereby emphasizes the need for a proper modeling of such disciplines within the multidisciplinary analysis and optimization framework. Nomenclature AR w = Wing aspect ratio, [-] BF = Block Fuel, lb BFL = Balanced Field Length, m BOW = Basic Operating Weight, lb CL max = Maximum lift coefficient, [-] HLR = Long-range Flight altitude, ft H p = Pressure altitude, ft IRR = Internal Rate of Return, % ISA = International Standard Atmosphere L/D = Lift-to-Drag ratio, [-] LFL = Landing field length (factored), m MLR = Long-range Mach number, [-] MTOW = Maximum Takeoff Weight, lb NBAA = National Business Aviation Association NPV = Net Present Value, miUS$ OEI = One Engine Inoperative Q = Total number of produced aircraft [-] SL = Sea level condition S w = Wing reference area, m 2 TOFL = Takeoff Field Length, m T SLS = Sea-Level Static Thrust, lbf T/W = Thrust-to-weight ratio, [-] W/S = Wing-loading, lbf/ft 2 W e /W 0 = Empty weight fraction of MTOW, [-] W f /W 0 = Fuel weight fraction of MTOW, [-] W f uel = Fuel weight, lb W payload = Payload weight, lb W resf = Reserve fuel weight, lb V2 = Obstacle clearance speed, knots f (.) = Objective function x = Vector of design variables g(.) = Vector of equality constraints h(.) = Vector of inequality constraints λ w = Wing taper ratio, [-] Λ w = Wing quarter chord sweep angle, deg f lap = Flap type slat = Slat type x sp1 = Spar 1 chordwise relative position, [-] x sp2 = Spar 2 chordwise relative position, [-]