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Climate functions for the use in multi-disciplinary optimisation in the pre-design of supersonic business jet

Published online by Cambridge University Press:  03 February 2016

V. Grewe ,
A. Stenke ,
M. Plohr  and
V. D. Korovkin
V. Grewe
Affiliation:
[email protected], Deutsches Zentrum für Luft- und Raumfahrt, Institut für Physik der Atmosphäre, Wessling, Germany
A. Stenke
Affiliation:
Institute for Atmospheric and Climate Science, ETH Zurich, Zurich, Switzerland
M. Plohr
Affiliation:
Deutsches Zentrum für Luft- und Raumfahrt, Institut für Antriebstechnik, Köln, Germany
V. D. Korovkin
Affiliation:
Central Institute of Aviation Motors, Moscow, Russia
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Abstract

Mitigation of climate change is a challenge to science and society. Here, we establish a methodology, applicable in multi-disciplinary optimisation (MDO) during aircraft pre-design, allowing a minimisation of the aircraft’s potential climate impact. In this first step we consider supersonic aircraft flying at a cruise altitude between 45kfeet (~13·5km, 150hPa) and 67kfeet (~20·5km, 50hPa). The methodology is based on climate functions, which give a relationship between 4 parameters representing an aircraft/engine configuration and an expected impact on global mean near surface temperature as an indicator for the impact on climate via changes in the greenhouse gases carbon dioxide, water vapour, ozone and methane. These input parameters are cruise altitude pressure, fuel consumption, fuel flow and Mach number. The climate functions for water vapour and carbon dioxide are independent from the chosen engine, whereas the climate functions for ozone and methane depend on engine parameters describing the nitrogen oxide emissions. Ten engine configurations are taken into account, which were considered in the framework of the EU-project HISAC. An analysis of the reliability of the climate functions with respect to the simplified climate-chemistry model AirClim and a detailed analysis of the climate functions is given.

Type
Research Article
Information
The Aeronautical Journal , Volume 114 , Issue 1154 , April 2010 , pp. 259 - 269
Copyright
Copyright © Royal Aeronautical Society 2010 

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