Preliminary Aerodynamic Shape Optimization of the SpaceLiner by Means of Engineering Methods

Abstract

An optimization routine has been implemented, validated and applied to improve the outer shape design of the DLR proposed SpaceLiner concept with engineering based aerodynamic tools including the estimation of aerothermodynamic loads. The routine consists of an aerodynamic approximation module based on Newtonian and additional engineering methods, a shape parameterization module to modify and mesh the geometry, and an optimization module based on a single-objective response surface methodology. The routine’s single components and the complete loop have been validated and tested to study their sensitivities. The optimization routine has been applied first to single components of the SpaceLiner to study sensitivities and influences of specific design parameters. Based on these studies the tool has been applied to the complete vehicle considering different flight conditions of a reference trajectory. The resulting shapes are evaluated for their longitudinal trim performance. An improvement in aerodynamic performance can be achieved especially in the hypersonic flow regime, which represents the major part of the trajectory.