Transcript NASA Green Aviation Challenge

David Axel Virzi
Marina Correia
William Tejada
The Challenge
 Design non-conventional aircraft to assist in the goals set
forth in the NASA metrics below
 Noise reduction, reduced fuel consumption, and weight
reduction
Problem Statement
 Aerodynamic design of a 200 passenger aircraft for
 Drag reduction
 Reduced fuel consumption
 Lower acoustic signature
 Weight reduction
 Incorporation of co-flow jet on a morphing wing to
assist in aforementioned requirements by
 Increased laminar flow
 Adaptability to various flight conditions
 Reduction of mechanical components
Conventional Aircraft
 Tube design is not the most aerodynamically efficient
design
 Design features several surfaces such as the vertical
and horizontal stabilizers that increase the overall
drag of the aircraft
 Passenger and cargo limitations – large aircraft such as
the Boeing 747 and Airbus A380 feature tall designs
that induce a lot of drag
Airframe Design Comparison
Type of Design
Drag Coefficient
Lift Coefficient
Fuel Efficiency
Acoustic
Signature
Maneuverability
Cargo Area
Conventional
Aircraft
Canard
Blended Wing
Body
Flying Wing
(A star signifies an option that best fits that category)
Canard Design
Flying Wing Design
Blended Wing Body Design
 BWB designs feature lower drag coefficients and
higher lift coefficients than conventional passenger
aircraft designs
 Unconventional designs can carry 800 passengers
while using 20-25% less fuel
Conventional Wings
 Conventional wings on passenger aircraft contain
thousands of moving parts that add weight and
contribute to difficulty in maintenance
 Control surfaces needed to control the aircraft cannot
adapt to different flight conditions
 Current control surfaces disrupt smooth airflow
Morphing Wings
 Can compensate for various flight stages
 Smoothly redirect airflow with minimal turbulence
and drag
 Overall weight can be reduced through elimination of
excessive mechanical parts
 In conjunction with carbon fiber reinforced
composites, wings can be designed to deform to their
desired shape
Actuation Design Alternatives
Method
Comments
Shape Memory Alloy
Easy shape design, low power required
Piezo-electric
Can be very small, high voltage required
Electromagnetic
Relatively large, require high force
Servo
Cheap, weak force for actuation
Shape Memory Alloy
Piezo-Electric Actuation
Co-Flow Jet
 CFJ flow control
significantly enhances
properties of lift and
drag
 Maintaining attached
flow reduces fuel
consumption and noise
emissions
Performance Metrics
Flight Condition
Altitude
Velocity
Metric
Take off
Sea Level
0 - VLO
Min Accel. Time
Climb 1
Sea Level
Vbest rate of climb
Max R.O.C.
Climb 2
30,000 ft
Vbest rate of climb
Max R.O.C.
Cruise 1
Sea Level
Vbest range
Max Range
Cruise 2
30,000 ft
Vbest range
Max Range
Acceleration
30,000 ft
M = 0.5
Max Accel.
Instant Turn
Sea Level
Corner Speed
Max Turn Rate
Sustained Turn
30,000 ft
Vbest turn rate
Max Turn Rate
Landing
Sea Level
Vapproach
Min Power
Timeline
The End
 Questions?