Strömungs- und Wärmeübergangsmessung für das zweistufige Raumtransportsystem ELAC
type: CreativeWork
description: In the future horizontally starting space transportation systems are going to replace vertically starting systems to bring men and material safely into space. These space shuttles act as lifting bodies, i.e. they take off and land like conventional airplanes. The two-stage space transportation system ELAC, defined within the framework of the Collaborative Research Center SFB 253, represents such a system and is being investigated experimentally and numerically in an academic research program. In the development of a space transportation system great significance is held by the flight stability and heat transfer analysis, which is influenced mainly by the flow around the shuttle. This work concentrates on visualization of the flow around the orbital stage and measurement of heat transfer. The visualization is achieved using color schlieren, differential interferometry, vapor-screen and oil film, whereas the heat transfer is determined with the liquid crystal display technique. Three-dimensional vortex systems of the lower stage (single delta wing) and the orbital stage (double delta wing) are presented for high angles of attack. Shock/shock interaction of the bow shock of the orbital stage with the embedded shock of the lower stage as well as shock/vortex interaction of the bow shock with the vortex system of the lower stage are explained. The separation of the orbital stage is strongly influenced by shock/shock and shock/boundary layer interaction which is hence investigated through flow visualization.
abstract: In the future horizontally starting space transportation systems are going to replace vertically starting systems to bring men and material safely into space. These space shuttles act as lifting bodies, i.e. they take off and land like conventional airplanes. The two-stage space transportation system ELAC, defined within the framework of the Collaborative Research Center SFB 253, represents such a system and is being investigated experimentally and numerically in an academic research program. In the development of a space transportation system great significance is held by the flight stability and heat transfer analysis, which is influenced mainly by the flow around the shuttle. This work concentrates on visualization of the flow around the orbital stage and measurement of heat transfer. The visualization is achieved using color schlieren, differential interferometry, vapor-screen and oil film, whereas the heat transfer is determined with the liquid crystal display technique. Three-dimensional vortex systems of the lower stage (single delta wing) and the orbital stage (double delta wing) are presented for high angles of attack. Shock/shock interaction of the bow shock of the orbital stage with the embedded shock of the lower stage as well as shock/vortex interaction of the bow shock with the vortex system of the lower stage are explained. The separation of the orbital stage is strongly influenced by shock/shock and shock/boundary layer interaction which is hence investigated through flow visualization.
author: Ting, Chen-Ching
language: ger
keywords: info:eu-repo/classification/ddc/620, Ingenieurwissenschaften, ELAC, EOS, Wärmeübergangsmessung, Flüssigkristallanstrich
date published: 2003
date modified: 2026-07-30T19:43:10Z
provider: RWTH Aachen University
publisher: Networked Digital Library of Theses and Dissertations
type: WebPage
source organization: Mainz