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Multi-Disciplinary Supersonic Transport Design

  • A. Van der Velden
Part of the International Centre for Mechanical Sciences book series (CISM, volume 366)

Abstract

The challenge in the development of a very complex system like a supersonic transport is not only to achieve the required technology, but also to link a team of highly skilled experts. In this paper a successful industrial approach is described to integrate the individual departments with their specific knowledge into the design of a future supersonic commercial transport.

Different designs are analyzed with a modular synthesis model and compared on the basis of operating economy with specified performance and environmental impact. The analysis routines of the synthesis model are mainly configuration independent and represent fixed levels of structural, aerodynamic and propulsion technology. The specialist departments are responsible for the content of the routines, and later verify the design with more refined methods. At present more than two hundred variables describe the aircraft geometry, engine characteristics and mission. Thirty of those variables representing the aircraft and its flight-profile are optimized simultaneously as a function of Mach number, payload and range. Because the various designs are analyzed with the same routines and optimization procedures they can be easily compared. This aircraft pre-optimization results in a significant reduction of the number of follow-on detail-design cycles, especially for non-conventional designs.

Examples are given for the preliminary design of arrow-wing and oblique wing supersonic aircraft as compared to subsonic aircraft using the same technology. It is also shown how technology and environmental constraints influence the sized design.

Keywords

Mach Number Wave Drag Aircraft Design Ozone Layer Depletion Noise Regulation 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

List of Principal Symbols

BPR

engine bypass ratio

CL

Lift coefficient

DEM

design empty mass

h

altitude

IOC

Indirect Operating Costs

M

Mach number

Mto

maximum takeoff weight

l

length

L/D

lift-to-drag ratio

OFW

oblique flying wing

OWB

oblique wing body

S

reference wing area

SCT

Supersonic Civil Transport

s.f.c.

specific fuel consumption (N/hr/N)

SLS

sea level static

SWB

symmetric wing body

t/c

thickness to chord ratio

TOC

total operating cost per seat km

Tt,4,max

maximum turbine entry temperature

Vmc

minimum control speed

w

width

εc,max

maximum engine pressure ratio

Λ

sweep angle

ΔO3

ozone depletion

ΔP

sonic boom sea-level overpressure

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Copyright information

© Springer-Verlag Wien 1997

Authors and Affiliations

  • A. Van der Velden
    • 1
  1. 1.Synaps Inc.AtlantaUSA

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