Jorge Martínez CfP11 Infoday Sevilla - REG IADP\r
From Clean Sky towards Clean Sky 2
• CS2 REG IADP objective is to bring the integration of technologies for regional
aircraft to a further level of complexity and maturity than achieved in Clean Sky
GRA. The global strategy is to integrate and validate, at a/c level, advanced
technologies for regional aircraft so as to drastically de-risk their integration on
future products:
Leonardo Aircraft:
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3
(**) Activities completed in 2019
Multimission TP 70 Pax
AG2 CIRA, ONERA, IMAST (*), HAI,SICAMB, SISW, FOXBIT (*), AEROSOFT, ITALSYSTEM, UMBRA, NOVOTECH, TECNAM, POLIMI, POLITO, UNINA, UNIPI
UMBRA, CERTIA, INSA, MAGNAGHI AER., POLITO, VIOLA
IRON CIRA, CENAERO NLR, ONERA, GRC, DOWTY GE, AVIO GE, TUD, POLITO, UNINA
ACITURRI, MTC, CAETANO AER.
D1 – Adaptive Wing Integrated Demonstrator
(Leader: Leonardo Aircraft) D1.1 – FLYING TEST BED#1 (FTB#1) Demonstration of LC&A and Aerodynamics enhancements
features through new generation wing devices and advanced FC
Actuation systems
(Leader: Airbus DS)
Integrated Technologies Demonstrator
Flight Demonstration of a high efficient and low noise Wing
with Integrated Structural and related Systems solutions
D1.2 – OWB Ground Demonstrator Structural static and fatigue tests of innovative
low cost and low weight structural technologies
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(Leader: Leonardo Aircraft) Full scale composite fuselage and passenger cabin with
innovative structural and architectural solutions aimed to weight
and cost reduction , methodologies and technologies for
innovative NDI, repair and maintenance, human centered
approach, comfort
Flight Simulator
(Leader: Leonardo Aircraft ) Integration and validation of FCS Load Control/Load Alleviation
(LC/LA), Electrical Landing Gear, Electrical Power Distribution
System, inter-system integration activity; support the
achievement of the permit-to-fly for FTB#1)
low cost and low weight structural technologies
integrated at full scale level
REG IADP Full Scale Demonstrators Master Plan – Major Milestones and TRL evolution
DEMONSTRATOR 2016 2017 2018 2019 2020 2021 2022
TRL3 TRL4 TRL5 TRL6
TRL4 TRL5 TRL6
D1.2 - Outer Wing Box (OWB)
D2 - Flying Test Bed#2 (FTB2)
D3.1 - Fuselage Structure
WP 4.1 Technology Assessment
RESULTS
Integrated Demo.
LDO VEL, CASA LDO VEL LDO VEL LDO VEL, CASA LDO VEL
Leonardo Aircraft (LDO VEL)
LDO VEL, AG2 LDO VEL
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WP 4.2 Ecodesign Interface
WP 2.2 Regional Avionics
WP 3.4 Iron Bird
(FTB2)
LDO VEL, ASTIB
LDO VEL, ASTIB
LDO VEL, FhG
JTI-CS2-2020-CFP11-REG-01-20
experimental testing methodologies for distributed electrical
propulsion
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Objectives:
It is proposed to develop technologies for experimental assessment of Distributed
Electrical Propulsion (DEP) aerodynamics and perform wind tunnel tests on a DEP
configuration using as reference a regional 40 Pax aircraft.
JTI-CS2-2020-CFP11-REG-01-20
OBJECTIVES:
Distributed electrical propulsion (DEP) can be used to improve
aircraft high lift performance. If properly designed DEP allows for an
increase of take-off and landing maximum lift coefficient therefore
resulting on a reduction of wing surface and aircraft weight.
The main objective of this CfP is to improve the physical
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The main objective of this CfP is to improve the physical
understanding of DEP technology for hybrid electrical aircraft:
Perform basic experimental studies to understand how DEP
propeller slipstream can increase airfoil maximum lift coefficient
Identify experimental techniques suited for DEP experimental
test
JTI-CS2-2020-CFP11-REG-01-20
It is proposed to test a 2D wing section, equipped with flap, and
with at least three propellers installed in front of the wing.
The wind tunnel experimental test should be aimed at
measurement on the central wing section lift, drag and moment
of:
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of:
JTI-CS2-2020-CFP11-REG-01-20
REQUIREMENTS:
Wing forces have to be measured separately from propeller forces. Internal
balance can be used, but alternative solutions can be proposed by the
applicant
it is necessary to measure force and moment of the wing section in the wake
of a single propeller in a DEP configuration.

Surface pressure measurements should be conducted with a sufficient span-
wise and chord-wise density to accurately determine where stall is initiating.
The applicant could also propose additional experimental technics for better
understanding of flow behind the propeller and the flap and identify flow
separation regions (e.g. PIV, oil flow, Pressure sensitive paint). All these
measurements techniques are not mandatory but will be considered as an
added value to the proposal.
JTI-CS2-2020-CFP11-REG-01-20
The reference configuration is a 40 seats regional aircraft. The
actual configuration design is not yet available, but it will be
provided before the project kick-off.
Anyway the provisional expected main characteristics of the
full scale configuration will be follows
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− Chord: 2.20 m
− Speed: 60 m/s
− Propeller thrust: 750 N, 1250 N, 1900 N
− Propeller diameters: 0,8 m, 1,3 m, 2,04 m
− Reynolds number based on chord: about 9 millions
It is expected that scaled test article will have a chord not lower than 0,8 m and
that the test should reproduce a Reynolds number of about 3.5 Million.
Nevertheless, to remain within the budget limitation, the applicant can propose a
smaller model scale and a smaller Reynolds number. In that case, evaluation of expected
uncertainties in the results should be provided.
The selected wind tunnel and model size should avoid blockage effect and wall/end plate
JTI-CS2-2020-CFP11-REG-01-20
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The selected wind tunnel and model size should avoid blockage effect and wall/end plate
negative interaction effect specially at high incidence and flap deflected.
The applicant has to:
1. Propose the best suited experimental arrangement and test article scale
2. Design and manufacture the test article
3. Provide engine and propellers
4. Perform wind tunnel test and measurement
5. Perform wind tunnel test data-analysis
JTI-CS2-2020-CFP11-REG-01-20
The following measurements/instrumentation is expected:
• Total forces and moments on the model measured by internal balance (Lift,
Drag, Pitching) on the model central part;
• At least 100 steady pressure taps on the model central section in two lines at
propeller side in the propeller wake;
• Propeller forces (Thrust and torque) on the central propeller measured with a
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• Propeller forces (Thrust and torque) on the central propeller measured with a
maximum resolution of 1 % of the mean thrust;
• Propeller rotation speed, measured with a resolution of maximum 0.1% of the
setpoint.;
• Sufficient repeat measurements should be conducted to quantify errorbars in
the delivered data.
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nacelles)
5 15° From -2
6 30° From -2
7 30° From -2
8 30° From -2
additional
diameters
JTI-CS2-2020-CFP11-REG-01-20
PROPOSED TEST MATRIX: OPTIONAL PART
ESSENTIAL TEST MATRIX
A3 15° From -2
additional
diameters
JTI-CS2-2020-CFP11-REG-01-20
Tasks description:
WP1: Management
The applicant has to set-up all classical project management structure and will be required
to organize periodic meetings (also by TELECON) with topic manager for project monitoring.
WP 2: Test set-up and test matrix
• The following parameters have to be addressed:
Two free stream speed
– Four propeller/wing relative position
– Two flap settings (with possible gap/overlap experimental optimization at least for one single propeller
power setting)
– Angle of attack up to stall plus 4° degrees
• To evaluate propeller installation effects, in addition to propeller-on tests, tests have to
be performed also with propeller-off configuration and nacelle off configuration (only
wing, that is, without nacelle and without propellers).
•
WP 3: Wind tunnel model design and manufacturing
• The applicant will be responsible to design and manufacture the model and provide all
required test instrumentation. The test article should have a chord not lower than about
0,8 meter (about 1 to 2,5 scale). Different scale model could be proposed depending on
budget requirements.
• The following requirements are expected to be satisfied:
– Propeller blade pitch (fixed pitch) set with an accuracy of 0.05 degree
– Surface roughness between 0.3 and 0.4 mu meter
– Angle of attack of the model within 0.02 degree
WP 4: Wind tunnel test performance
• The applicant will be responsible for test execution and to provide test engineering.
JTI-CS2-2020-CFP11-REG-01-20
WP 5: Wind tunnel test data-analysis
• The applicant will be responsible of test data analysis. Raw data processing and wind
tunnel correction compliance with wind tunnel expertise have to be provided.
• The applicant has also to provide forces and moment acting on the wing central part
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• The applicant has also to provide forces and moment acting on the wing central part
without propeller forces.
• Therefore the following separated data-set have to be provided for each test conditions:
– Propeller forces, moment and power
– Central wing forces and moment
– Flap moment and forces (only for deflected flap configuration).
JTI-CS2-2020-CFP11-REG-01-20
M1 (WP2) Experimental set-up definition R T0+6
M2 (WP3) Test article design R T0+9
M3 (WP3) Test article manufacturing H T0+18
Performance of wind tunnel tests
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M4 (WP4) Performance of wind tunnel tests D T0+20
M5 (WP5) Test report R T0+24
JTI-CS2-2020-CFP11-REG-01-20
Milestones:
Deliverables
Del 1.1 Technical Progress report R T0+12
Del 1.2 Final Technical Progress R T024
Del 2.1 Experimental set-up definition R T0+6
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Del 2.2 Wind tunnel test matrix and test requirements R T0+6
Del 3.1 Test article design R, D T0+9
Del 3.2 Test article manufacturing H T0+18
Del 4.1 Preliminary Test report (raw data) R, D T0+20
Del 5.1 Final Test report (corrected data) R, D T0+24
JTI-CS2-2020-CFP11-REG-01-20
– Consolidated experience in wind tunnel test technical management.
– Knowledge of wind tunnel test measurement techniques.
– Experience in Wind tunnel test activities, data analysis and reporting.
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– Experience in Wind tunnel test activities, data analysis and reporting.
• Advantageous:
– Expertise in PIV/PSP measurement techniques
Indicative Funding Topic Value: 800 K€
Duration of the action: 24 Months
Type of Agreement: Implementation Agreement
Title
Thank You
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