HIgh Speed AirCraft (HISAC)...This document is the property of the HISAC consortium and shall not be distributed or reproduced without the formal approval of the HISAC coordinator

1This document is the property of the HISAC consortium and shall not be distributed or reproduced without the formal approval of the HISAC coordinatorVienna 19 / 06 / 2006

HIgh Speed AirCraft (HISAC)

A European `` Integrated Project’’


Agenda

HISAC Composition and Objectives

Main Design ProblemsWork OrganisationGeneral Progress


HISAC PARTNERS

Dassault AviationAlenia AeronauticaCFS EngineeringEADS DeustchlandRolls RoyceRUAG AerospaceSukhoï Civil AircraftSENERSNECMA SONACAVolvo Aero Corp.

ADSEESTECOIBKINASCONUMECA

ARACIAMCNRSDLRFOIINRIAIoAITAMNLRONERATsAGI

EUROCONTROL

ChalmersCranfieldECL LMFAEPFLISVRKTHNTUATCDNapoli

37 Partners from 5 sectors

Industry SME ResearchCenters

Universities

Others


05_DV_096_01

HISAC PARTNERS

37 Partners from 13 countries

DASSAVECL LMFAONERASMCNRSINRIA

DASSAVECL LMFAONERASMCNRSINRIASENERSENER

RRUKARACUISVR

RRUKARACUISVR

TCDTCD

ALAUni-NA DPAESTECO

ALAUni-NA DPAESTECO

EADS MIBKDLR

EADS MIBKDLR

IoAIoA

INASCONTUAINASCONTUA

VOLVOFOIChalmersKTH

VOLVOFOIChalmersKTH

SCACIAMTsAGIITAM

SCACIAMTsAGIITAM

ADSENLRADSENLR

SONACANUMECAEEC

SONACANUMECAEEC

CFSRUAGEPFL

CFSRUAGEPFL


HISAC General Objectives

Technically Feasible

Environmentally Compliant

Supersonic

Small Size Transport Aircraft


Agenda




Subsonicclimb

TransonicAcceleration

Supersonic climb& acceleration

Cruise

Descent

Take off Landing

RANGE > 3500 NM

OPERATIONS FROM REGIONAL AIRPORT

SONICBOOM

EMISSIONS N0x

NOISE

Reserve

Main Design Problems


LOS ANGELES

BUENOS AIRES

RIO DE JANEIROJAKARTA

BANGKOK

CALCUTTA

DARWIN

BANGUI

ADDIS ABABA

KARACHI

MUSCATJEDDAH

RIO DE JANEIRO

SYDNEYBUENOS AIRES

LOS ANGELES HONG KONG

SINGAPORE

6500 nm - M = 0.80≈ 14 hours

2 x 4000 nm - M =1.8≈ 8 hours

Design Problems:Range

GLOBAL JETS reach business jets range limit:

~ 6500 nm @ Mach = 0,8time ~ 14 hours

Demand for travel time reduction:

-20% to 50%


Design Problems:Sonic boom

0

20

40

60

80

100

120

140

0 50 100 150 200 250 300Mass (tons)

Boom Intensity∆P max (N/m²)

CONCORDESSBJ

QSP TARGET : ACCEPTABLE NOISE LEVEL?

2 psf

0,3 psf

Is the achievable boom mitigation compatible with overland flight ?

A/C Weight & Size

AltitudeAchievable Target :

max overpressure 1 psf

Shaping

2/3 reduction of initialoverpressure?

Robust to :- cruise altitude ?

- atmospheric tubulence ?

Boom shaping


Breguet-Leduc formula:

Lift/Drag Ratio : Aerodynamic performanceTSFC : Specific Consumption – Engine Performance

Mi/Mf : Structural index -- MFuel/Mtow need ( around 50%)

Lift/Drag ratio End of climb weight Range = ---------------------- x ln --------------------------- x V TSFC End of cruise weight

Supersonic Design Problems


Supersonic Lift to Drag ratio

Same Span over Fuselage Diameter Ratio

SSBJ

Concorde

Improvement in L/D requires low wing thickness


Noise / Fuel Consumption

Optimal Supersonic By Pass Ratio near to 0!Classical Subsonic By Pass Ratio above 4!

1. Aircraft : Engine Integration Drag minimisation2. Engine : Variable geometry and Mixer-Ejector

How to reduce the impact of this constraint ?


Some Structural Ratios (Mfuel / MTOW):

Robustness / Sensitivity

• Concorde : 0.52• Tupolev 144 : 0.5• SSBJ : 0.53

• Airbus A320 : 0.26• Falcon 2000 : 0.33• Falcon 2000 EX Easy : 0.40

High Sensitivity of the General Performancesto Uncertainties


Feasibility without any Major Engine TechnologicalStep will require:

• Very low wing thickness• Efficient aerodynamic engine integration

Quality and Precision of Evaluations are Key Factors

Supersonic Design Problems


Approach speed is the other major constraint

Following aspects have to be analyzed:

• Angle of attack at landing (visibility constraint aspects)• High lift device performances• Approach instability : flap additional lift

Subsonic Design Problems


Agenda




HISAC General Logic

3 TEAMS/ 1 BENCHMARK CASE

Models, Tools & Methods - WP2(Noise, Emission, Sonic Boom, Engine, Aerodynamic, MDO)

Environmental Objectives & Constraints - WP1(Community noise, Emissions, Sonic boom Criteria)

Integration and Aircraft Definition (WP 4 & 5)

Engine key technologies - WP3A(Variable Cycle Engine, Nozzle Noise reduction)

Airframe key technologies -WP3B(Forced laminar flow, high lift devices,variable geometry wing)


Requirements for First Loop


a

Main milestonesof the HISACproject

WP1

WP2

WP3

WP4

WP5

Year 2 Year 3 Year 4Year 1T 13 T 14 T 15 T 16T 9 T 10 T 11 T 12T 5 T 6 T 7 T 8T 1 T 2 T 3 T 4

specific & global designsyntheses

trade-off studies trade-off studies

requirementsupdate

&teamsreorientations

SelectionoftheAircraft

ConfigurationFamilies

Initial modelling Modelling developpment Modelling support & updates

Key TechnologySelection

Key technologies studies & assessments

Models construction & tests

Key technologiessyntheses

Initial objectives Environmental objectives & criteria Environmental impact assessments

Detailed shapes

Models construction & tests

Numerical / experimental assessmentsKey integration

syntheses

MDO Methods MDO Bencharking

First Iteration Designwith available MDO process

Third Iteration Designwith improved MDO process

requirementsupdate

&teamsreorientations

Second Iteration Design with improved MDO process

Global acoustic, sonic boom &aerodynamic concepts

Decision PointDecision Point

MilestoneM6

MilestoneM18

MilestoneM30

MilestoneM42

Administrativedecision point

M12


M24


M36

4 year study

HISAC Break Down

26 MEuros


Planning

WS1 WS2

Oct 2005July 2005

May 2005

T0

End of Phase 1

November 2006WS3

March 2006

Reference Configuration choice (10th March, 2006)

Detailed external shape definition

Derivatives studies

Tools and Models

Cross check evaluations

Today


Agenda




Team A : Dassault

39000


Team B : Alenia

Long Range Concept(Laminar wing shape)


Team C : Sukhoï

Configuration 2(variable geometry)

Configuration 3

Configuration 1(low boom)


Reference Configuration

Support for Key Points Feasibility study

Support for the crosscheck between the 3 Teams

•Models and Tools benchmarking•Uncertainties reduction

Starting point for Wind Tunnel Models definition

This configuration is not supposed to be the final one.


Reference Configuration


HISACReference Configuration is now defined

Next main milestone is October 2006:– Environmental Studies Results ( WP1 )– First Set of Tools Development ( WP2 )– First Results of Technology Studies ( WP3 )– Aerodynamic Models Definition ( WP4 )– First Results of Cross check and Update of Requirements for

the Second Loop ( WP5 )


HISACA very ambitious project for Europe :

• Cooperation: 37 partners, 5 sectors, 13 countriesincluding Russia

• High technology product• Economically viable and Environmentally

compliant


END


Work ProgrammeExpected outcome

Environmental objectivesNoise ICAO Chapter 4 less 8dBNOx emissions High altitude:less than 10g per kg fuel burnt (5g in the long term)

At landing and take-off: comparable to subsonic aircraftSonic boom less than 15 Pa (tbc) differential pressure (overland flight)Commercial characteristics objectivesSize of cabin 8 to 16 passengersSpeed transonic to M 1.8Range 3500 to 4500 nm (~6000 to ~9000 km)Airfield length 7000 ft

HISAC Quantified Objectives:

Documents

HIgh Speed AirCraft (HISAC)...This document is the property of the HISAC consortium and shall not be distributed or reproduced without the formal approval of the HISAC coordinator