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Numerical Analysis of the Aerodynamic Performances of three Different SpaceLiner Configurations

Buffetti, Barbara (2012) Numerical Analysis of the Aerodynamic Performances of three Different SpaceLiner Configurations. Master's, Politecnico Milano.

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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.

Item URL in elib:https://elib.dlr.de/78299/
Document Type:Thesis (Master's)
Title:Numerical Analysis of the Aerodynamic Performances of three Different SpaceLiner Configurations
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Open Access:No
Number of Pages:104
Keywords:SpaceLiner, aerodynamic analysis, CFD, hypersonic, blunt trailing edge
Institution:Politecnico Milano
Department:Facolta di Ingegneria Industriale
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transportation
DLR - Research area:Raumfahrt
DLR - Program:R RP - Space Transportation
DLR - Research theme (Project):R - Raumfahrzeugsysteme - Systemanalyse Raumtransport (old)
Location: Köln-Porz
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Über- und Hyperschalltechnologien
Deposited By: Neeb, Dominik
Deposited On:14 Nov 2012 09:41
Last Modified:18 Oct 2013 14:35

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