The creation of a parameterized, multi-fidelity fighter aircraft geometry for MDAO studies is presented. Using CAPS, the geometry can be directly output to analyses of multiple fidelities ranging from linear panel methods to RANS. The planform is parameterized using 21 total parameters accounting for the shape of wings and tails, fuselage scaling, control surface deflections, and desired output fidelity. The parameterization is centered around the F-16 planform and baseline analysis results are presented and compared to published wind tunnel data. Finally, an MDAO implementation focused on controllability is presented with initial results.

A comparative analysis of aerodynamic modeling techniques for potential use in the multidisciplinary design optimization (MDO) of next generation Efficient Supersonic Air Vehicles (ESAVs) is presented. These vehicles will likely be tailless, with unique challenges in lateral control requiring the use of multiple unconventional control effectors. However, with no previous examples and no empirical knowledge in which to base these designs, the analysis of these effectors must be validated. In addition, for inclusion in the overall design optimization routine, the analysis must balance a tradeoff between fidelity of the solution and computation time. This paper explores this tradeoff, comparing multiple analysis techniques, ranging from linear panel methods to Reynolds averaged Navier-Stokes solutions. The paper applies these tools to a representative ESAV with different forebody shapes. Additionally the impact of body tabs deployed on these different forebody configurations is investigated. Finally the required control authority to meet level one flying qualities is quantified and compared to that available for each configuration. Nomenclature= pitch moment coefficient at zero degrees angle of attack = pitch moment coefficient derivative with respect to angle of attack = angle of attack required for trimmed flight = pitch moment coefficient required for trimmed flight = frequency of short period mode = damping ratio of short period mode = augmented pitch stiffness required to meet short period flying qualities requirements , , = moments of inertia = dynamic pressure , , = reference wing span, chord, area = body axis dimensional vertical force derivative with respect to angle of attack = freestream total velocity = commanded angle of attack = pitch moment coefficient required to command an angle of attack 2 = commanded g-loading = aircraft weight = lift curve slope = gust velocity = angle of attack change due to vertical gust = pitch moment coefficient required to reject vertical gust = roll moment coefficient required to meet rolling flying qualities requirements = roll angle = dimensional roll moment derivative with respect to roll rate = yaw moment coefficient required for roll initiation = yaw moment coefficient derivative with respect to roll rate = roll moment coefficient derivative with respect to roll rate = pitch moment coefficient required for roll coordination = roll rate = augmented yaw moment derivative with respect to sideslip required for dutch roll = frequency of Dutch roll mode = damping ratio of Dutch roll mode = dimensional yaw moment derivative with respect to sideslip = sideslip angle change due to lateral gust = yaw moment coefficient required to reject lateral gust = yaw moment coefficient derivative with respect to sideslip = sideslip angle due to crosswind = yaw moment coefficient required to overcome crosswind = roll moment coefficient derivative with respect to sideslip = roll moment coefficient required to overcome crosswind

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