In this article design and optimization scheme of a three-dimensional bump surface for a supersonic aircraft is presented. A baseline bump and inlet duct with forward cowl lip is initially modeled in accordance with an existing bump configuration on a supersonic jet aircraft. Various design parameters for bump surface of diverterless supersonic inlet systems are identified, and design space is established using sensitivity analysis to identify the uncertainty associated with each design parameter by the one-factor-at-a-time approach. Subsequently, the designed configurations are selected by performing a three-level design of experiments using the Box–Behnken method and the numerical simulations. Surrogate modeling is carried out by the least square regression method to identify the fitness function, and optimization is performed using genetic algorithm based on pressure recovery as the objective function. The resultant optimized bump configuration demonstrates significant improvement in pressure recovery and flow characteristics as compared to baseline configuration at both supersonic and subsonic flow conditions and at design and off-design conditions. The proposed design and optimization methodology can be applied for optimizing the bump surface design of any diverterless supersonic inlet system for maximizing the intake performance.

本文提出了一种超音速飞机三维凹凸表面的设计与优化方案。首先根据超音速喷气飞机上现有的碰撞配置对带有前整流罩唇的基线碰撞和进气道进行建模。识别了无分流超音速进气系统的凹凸表面的各种设计参数，并通过敏感性分析建立了设计空间，以通过一次一因素的方法识别与每个设计参数相关的不确定性。随后，通过使用Box–Behnken方法和数值模拟执行三级实验设计来选择设计的配置。替代模型是通过最小二乘回归方法进行的，以识别适应度函数，利用压力恢复为目标函数的遗传算法进行优化。与在超音速和亚音速流动条件下以及在设计和非设计条件下的基线配置相比，所得到的优化的凸块配置在压力恢复和流量特性方面显示出显着的改善。所提出的设计和优化方法可以用于优化任何无分流超音速进气系统的颠簸表面设计，以使进气性能最大化。