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Copyright © 2012 Boeing. All rights reserved, Government Purpose Rights.
Engineering, Operations & Technology | Boeing Research & Technology Blended Wing Body | X- 48C
X-48C_Template.ppt | 1
Flight Testing the X-48C Advancing the BWB Concept
Michael Kisska X-48C Project Manager
(714) 896-1464
AIAA Southern California Aerospace Systems and Technology Conference
May 4, 2013
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Engineering, Operations & Technology | Boeing Research & Technology Blended Wing Body | X- 48C
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-33%
Conventional Aircraft Blended Wing Body
Wetted Area Comparison
Fuselage 23,000 ft2 22,000 ft2
Wing 12,000 ft2 6,000 ft2
Propulsion 4,000 ft2 1,200 ft2
Empennage 5,000 ft2 500 ft2
Total 44,000 ft2 29,700 ft2
1/3 less wetted area than conventional configuration
Why BWB? - Aerodynamic Efficiency
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Span loading
Non-lifting vs lifting fuselage
Independent vs integrated wing box
Payload distributed normal vs parallel to wing
Ideal circular vs flat pressure vessel
Conventional Aircraft Blended Wing Body
Aerodynamic Lift
Pressure Loads
Why BWB? - Structural Efficiency
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BWB Technology Development Background
Low-Speed Wind
Tunnel Test
BWB 450-1L Low-Speed
Wind Tunnel Test
Piloted
Simulation
X-48B Built
BWB-17 Flight
Control Testbed
High-Speed Wind
Tunnel Test (NTF)
Finite Element
Analysis
Computational
Fluid Dynamics
High-Speed Wind
Tunnel Tests (NTF)
Structures Panel Fab Free-Flight Test
5% Model
X-48B Wind Tunnel
Test (30x60)
1997 1998 1999 2000
2001 2004 2005 2006
2007
PRSEUS Structure HS Wind Tunnel Test
(AEDC 16T)
X-48B Flight Test
2010 2012 2013
X-48C Wind Tunnel
Test (30x60)
X-48C Flight Test PRSEUS CoLTS
Test Article
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8.5% Dynamically Scaled X-48B BWB
Vehicle Characteristics
Wing Span 20.4 ft
Wing Area 100.5 ft2
Maximum Weight 523 lbs
Static Thrust 162 lbs
Maximum Airspeed 118 kts
Maximum Altitude 10,000 ft MSL
Load Factor Limits +4.5 g’s to -3.0 g’s
Flight Duration 30 minutes + 5 minute reserve
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X-48B Low Speed Vehicle
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Definition of Test Flight Blocks
Block 1: Flights 1-11
Slats EXT
Block 2: Flights 12-20
Slats RET
Block 3: Flights 21-34, 44-56, 59-61, 67-70
Slats EXT
Block 4: Flights 35-43, 57-58, 62-66, 71-72
Slats RET
En
ve
lop
e E
xp
an
sio
n
PID / Stalls /
Engine Out
Maneuvering
Block 5: Flights 73-75, 77
Slats EXT
Block 6: Flights 76, 78-80
Slats RET Departure Limiter
Assaults / Turning
Stalls
Currently moving
forward Single
Surface PID and
additional RTSM
Maneuvers to fly
on Recycle Decks
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X-48B Flight Test Program – Success!
Project initiated in 2002
Airplanes designed by Boeing, built by Cranfield Aerospace, and operated at NASA Dryden
Objective to prove that flight characteristics of a BWB are as robust as current transports
1st Flight on July 20, 2007
80 flights completed in Phase 1 Program
Completed all flight test conditions originally planned - met expectations
Final Report submitted on May 28, 2010
Aircraft underwent a detailed airworthiness inspection and heavy maintenance
12 additional test fights NASA Phase 1.5 experiments conducted in 4Q10 – 92 flights completed
Phase 1.5 Completed on Nov 25, 2010
Several NASA Authored AIAA Papers presented in 2011
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X-48B Preliminary Flight Test Results
Extremely maneuverable in roll
Aircraft very closely matches sim for up/away flight (and landing)
Flight control design is very robust
Both Slat EXT and Slat RET stalls successful
• Controllable to 3 degrees beyond CLmax
Departure limiter assaults highly successful!
Overall, the aircraft flies extremely well…
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NASA N+2 – X-48C Inspiration…
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X-48C Low Emission Concept Evolution
Twin AMT Titan
turbojet engines
mounted further
forward on the
centerbody Inboard Vertical
Stabilizers –
Revised Elevon 1
Winglet Rudders
removed –
conventional
wingtips
Revised VMS
Flight Control
Software
X-48B
X-48C
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X-48C Flight Test Vehicle
12
Description:
The X-48C is a modification of the X-48B
designed to investigate the stability and control
of the “Low Emissions Concept” BWB
configuration.
Goals/Objectives:
To aerodynamically characterize the revised
BWB configuration to validate the vehicle’s
simulation model. Characterization will be
assessed via dynamic maneuvers flown at
multiple CGs including: PID, SHSL, Stalls,
Doublets and Frequency Sweeps while
simultaneously verifying the revised elements
of the vehicle’s control laws.
Success will be achieved when the vehicle’s
flight envelope is defined.
Project Schedule - Key Milestones/Deliverables:
Initial Design
and Sizing
Studies
Design for WT
Testing Vehicle
Engineering
and Fab of Flit
Components
1st Flight
8/7/12
2010 2009 2008 2011 2012 2013
Complete
Flight Testing
Issue Final
Report in Q2
Complete WT
Testing and
Issue Report
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Validating Critical Flight Control Technology
Intend to characterize the X-48C flight envelope
B-2
pre-stall
a limit CL
a
BWB
post-stall
a limit
Performance gain –
reduced wing area
and weight
CM Stable Unstable
Increased challenge to maintain control in unstable post-stall region
Controllable in
post-stall region
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X-48C in Langley Full Scale Tunnel – Aug. 2009
14
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SPT15 Engine Development
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AMT Titan Engine Installation
ECU
Fuel Pump
Engine CMD
PumpV
Throttle
CMD
Sensor
output
Thrust FCC
Fuel Flow
Propulsion
System
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First Flight! August 7, 2012
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X-48C 2012-2013 Milestones
2012
Jan X-48C “Mass Correct” Vehicle Assembled
Jan GVT/SMI successfully Completed
Mar Engine Mapping & Software Development
Apr First Flight VMS Software Released
May First Flight Readiness Review
Aug First Flight
Aug-Sep eRCCA
10/9/12 Successful Return to Flight
Oct-Dec Flights 3-13 (Envelope Expansion)
2013
Jan Return to Flight - Flight 14
Jan-Apr Flights 14-26
April Completion of Flight Testing
Note: Continued work planned throughout 2Q13 to complete flight testing, document and publish Final Report
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Definition of Test Flight Blocks
Block 1: Flights 1-12
Slats EXT
Block 2: Flights 12-17
Slats RET
Block 3: Flights 25-
Slats EXT
Block 4: Flights 18-24
Slats RET
En
ve
lop
e E
xp
an
sio
n
PID / Stalls /
Engine Out
Maneuvering
Block 5:
Slats EXT
Block 6:
Slats RET Departure Limiter
Assaults / Turning
Stalls
Due to time constraints,
Block 4 maneuvers were
performed immediately
after Block 2 in order to
eliminate the additional
configuration change.
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X-48C Preliminary Flight Test Results
Remains extremely maneuverable in roll
Aircraft again very closely matches sim for up/away flight (and landing)
First Cut flight control design is very robust – but further gains could be realized with future software roll…
Both Slat EXT and Slat RET stalls successful
• Controllable to 2 degrees beyond CLmax…but CLmax was higher with the X-48C configuration
Overall, the data related to the configuration appears to be encouraging and merits additional study…
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Poster Child!
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Additional Images Featured in Print
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And Finally…Pop Culture Icon!
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And Chase Mascot!
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