Numerical Analysis of the Aerodynamic Performances of three Different SpaceLiner Configurations

Abstract

The SpaceLiner4-3 (SL) configuration is planned to be experimentally assessed during wind tunnel tests. However, the original design of the SL4-3 foresees wing and profiles with a sharp trailing edge, which cannot be manufactured for a wind tunnel model. Therefore, the wing and geometries need to be modified to satisfy the constructive requirement of trailing edges with finite thickness. The aim of the present work is to numerically investigate the aerodynamic performances of two configurations with the wing airfoils differently thickened, in order to select the wind tunnel model geometry which performs more closely to the original design with sharp trailing edges. The numerical tools used for the investigations are the flow solver TAU and the software HOTSOSE. In the first modified configuration, the thickening is performed symmetrically with respect to the mean chord. On the other hand, for the second configuration, the thickening is realized only on the upper side of the wing, therefore in an unsymmetrical way. Simulations are run for the two blunt versions and for the original configuration in order to perform a comparative aerodynamic analysis. Preliminary 2D calculations are considered for profiles related to each configuration and run for a viscous flow at different flow conditions. The following 3D investigations are accomplished for an Euler model at M = 2, considering the angles of attack of 0° and 5°. Due to numerical convergence problems, the simulations at 0° angle of attack are performed with unsteady calculations. The analysis of the aerodynamic coefficients shows that the symmetric blunt configuration has an aerodynamic behavior which is closer to the one of the original project and is therefore to be favored for the wind tunnel tests.