Design of Morphing Wings By Vijay K. Goyal, PhD

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Design of Morphing WingsBy Vijay K. Goyal,
PhD
Department of Mechanical Engineering
On May 4, 2004 at 430 PM in L-242
[phone] x-2111 or by email
vgoyal_at_me.uprm.edu
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Morphing Plane Wings for Efficient Flights
Airplanes, whether manned or unmanned, need to
travel at various speeds. For example, a
surveillance plane needs to fly fast to reach its
destination point. It needs to reduce its speed
to achieve its surveillance mission.
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Morphing Plane Wings for Efficient Flights
Airplane wings that change shape like a bird and
have scales like a fish. Airplanes today are a
design compromise. They have a fixed-wing
structure that is not ideal for every part of a
typical flight. Being able to change the shape
of the wings to reduce drag and power, which vary
with flight speed, could optimize fuel
consumption so that commercial planes could fly
more efficiently.
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Morphing Plane Wings for Efficient Flights
Flying efficiently at high speed requires small,
perhaps, swept wings. Flying at slow speed for
long periods requires long narrow wings.
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Morphing Plane Wings for Efficient Flights
ON A BENDER. With a bone-and-muscle-like wing
structure beneath flexible skin, this concept for
a morphing aircraft mimics bird flight
behaviorsthough not flapping. NASA predicts an
aircraft like this may fly by 2030.NASA
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Wings
Croot
Ctip
Span
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Wings Span
Span is the length from left tip to right tip of
the wing across the fuselage.

• SPAN is constraint by Hangar size Ground
  facilities Span increases wings structural
  aspect increases

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Wings Area

• Based on Lift/Drag Stalling Speed/Field Length
  Wing Weight Aero elasticity Divergence
  Vibrations

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Wing Area
                                                
                                                  
                                  span x (root
chord tip chord)/2 area
                                                
                                                  
                                  span x
(root chord tip chord)/2 area
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Wings Aspect Ratio

• AR b/c Ratio of the span to average chord
  High AR Longer Wing Span High AR Displaces
  more air and might decrease drag

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Common aspect ratio
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Challenges

• Find a non-dimensional parameter to determine the
  wings efficiency to compare morphing wings with
  regular wings.

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Basic Forces
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Lift/Drag ratio

• Is the measured of the aerodynamic efficiency of
  the aircraft.
• L/D ratio improves rapidly between 0 - 5

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Lift/Drag Ratio

• The lift and drag of an airfoil depend
• The shape of the airfoil
• The plan area of the airfoil (or wing area).
• The square of the velocity (or true airspeed).
• The density of the air.

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Other Considerations
Stalling Every aircraft has a minimum speed it
needs to maintain flight. This value is called
the stall speed, because a stall will occur if
the plane's velocity falls below it.
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Thickness

• The Thickness ratio (t/c) refers to the maximum
  thickness of the airfoil divided by its chord.
• Greater t/c increases fuel volume.

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Thickness
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Thickness

• The drag increases with increasing
• thickness due to increased separation.

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Thrust to weight ratio (T/W)

• An aircraft with a higher T/W will accelerate
  more quickly, climb more rapidly, reach a higher
  maximum speed.

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Thrust to weight ratio (T/W)

• The thrust to weight ratio indicates how
  efficient total aircraft propulsion is.
• An aircraft with a high thrust to weight ratio
  has high acceleration.
• Most Combat aircraft have between 0.7 to 0.9.

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Thrust to weight ratio (T/W)
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Efficiency

• The lift to drag ratio is an efficiency parameter
  for the total aircraft aerodynamics.
• The thrust and weight ratio is an efficiency
  factor for total aircraft propulsion ( Thrust
  efficiency of the engine).

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New Efficiency
GAD (T/W)(AR) (L/D) ? 1- GAD
Boeing 757-300 D.A.G1 (T/W)(AR) L/D
0.3196(7.8)
17 D.A.G1 0.1464 ? 1- D.A.G1 1-0.1464
? 0.8536
Boeing 747-400 D.A.G1 (T/W)(AR) L/D
0.2867(7.39)
17 D.A.G1 0.1246 ? 1- D.A.G1 1-0.1246
? 0.8753
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Boeing 757-300 D.A.G1 (T/W)(AR) L/D
0.3196(7.8)
17 D.A.G1 0.1464 ? 1- D.A.G1 1-0.1464
? 0.8536
Boeing 747-400 D.A.G1 (T/W)(AR) L/D
0.2867(7.39)
17 D.A.G1 0.1246 ? 1- D.A.G1 1-0.1246
? 0.8753
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For Boeing 747
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For Boeing 757
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Boeing 767 300ER
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Questions