基于离散型伴随方法的单边膨胀喷管优化设计研究 postprint

Abstract: At present, the characteristic line method and the optimization method based on the CFD analysis arethe mainly methods for hypersonic nozzles designing. However, the characteristic line method can’t come overthe shortcoming of the assumptions that the flow is no-viscosity and no-rotation. Besides, the genetic algorithmand general gradient-based algorithms used for hypersonic nozzles designing can’t handle the challenges ofincreasing number of design variables. Considering the calculation cost of the adjoint method isn’t sensitivewith the number of design variables, this paper uses the discrete adjoint method to design the unilateralexpansion nozzle, accomplishing the parametric model of controlling the area distribution of the nozzle alongthe streamline. On the base of the initial nozzle designed by the genetic algorithm, which already has the greatperformance, the optimization can improve the thrust coefficient with 0.8 percentage points.