Tailoring wing structures for reduced drag penalty in off- design flight conditions Melih Papila Raphael T. Haftka Sabanci University, Turkey University of Florida SPONSOR: NASA Langley Research Center William H. Mason Virgina Tech. Rafael Alves Instituto Tecnologico de Aeronautica, Brasil
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Tailoring wing structures for reduced drag penalty in off-design flight conditions Melih Papila Raphael T. Haftka Sabanci University, Turkey University.
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Tailoring wing structures for reduced drag penalty in off-design
flight conditions
Melih Papila Raphael T. HaftkaSabanci University, Turkey University of Florida
SPONSOR: NASA Langley Research Center
William H. MasonVirgina Tech.
Rafael AlvesInstituto Tecnologico de Aeronautica, Brasil
2
Motivation
Airplanes are prone to frequent deviations from cruise design condition during service life.
The wing of an airplane is not optimal with respect to induced drag at all flight conditions as the structural deformation and the effective twist change
The drag penalty for flight at off-design conditions can translate to thousands of gallons of jet fuel over the lifetime of an airplane.
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Motivation-Analytical proof
Given a rigid wing planform
Assume minimum induced drag for two different lift coefficients (elliptic circulation or spanload) associated with two different angles of attack. )1()( )2()(
)1(LC
)2(LC
sin)1()1( A sin)2()2( A
)2()1(
Constant angle of incidence (no twist)
)2()1(
Elliptic circulation
Elliptic circulation
Constant angle of incidence, along the span (no twist) and elliptical circulation is only possible if the wing also has an elliptic chord distribution Elliptic circulation
Difference
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Objectives
Demonstrate the effect of fixed geometric wing twist on induced drag due to change in flight conditions
Compare with a wing of variable twist as the flight condition changes
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Outline
Motivation and objectives Example wing problem Approach Analysis models Results
for near elliptic distribution for straight-line wrapped surfaces
Given spanload, LIDRAG (FORTRAN code from Virginia Tech) computes span efficiency e and total lift coefficient CL
Local lift-coefficient
Spanload
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Rib Shear web
Spar Shear web
Skin panel
Rib caps
Spar caps
Analysis for induced drag penaltyStructural model
MSC.NASTRAN structural model Leading and trailing edge spars Fifteen equally spaced ribs
Upper and lower skins are assumed identical
Each bay has uniform thickness for structural optimization: 14 skin panel thicknesses variables.
Structural optimization: minimize weight under stress constraints (a load factor of 2.5 on the dynamic pressure and a safety factor of 1.5 on the stress allowable)
Young’s modulus, E (GPa) 70 Poison’s ratio, 0.33
Allowable stress, all (MPa) 489
Density, (kg/m3) 2769
Aluminum
140
1
2
3
4
5
6
7
8
0 0.2 0.4 0.6 0.8 1eta
op
tim
al t
ot.
an
gle
of
inc
ide
nc
e (
de
gre
e)
des ign condition
off-des ign condition
Near elliptic distribution
Recall the goal: assess performance of optimal geometric wing twist at off-design condition.
Optimal total angle of incidence via Aerodynamic Analyses, LAMDES.
Total angle of incidence
flight path
)(tot
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Induced drag penalty- Rigid wing
Near elliptic distribution
Design condition (1)
Optimal wing Off-design condition (2)
Optimal wing Off-design condition (2)
Non-optimal wing
Lift coefficient, LC )1(LC = 0.6
)2(LC = 0.42
)2(LC = 0.42
Span efficiency, e )1(maxe = 0.99736 )2(
maxe = 0.99738 )2(e = 0.99884
Induced drag
coefficient, iD
C
0.01539
0.00751
0.00749
Induced drag penalty
)2(max
)2()2(max
e
ee = -0.004
Attributed to LAMDES not finding true optimum or true elliptic spanload, but near optimal.
How the structural deformation will affect results?
ARe
CC LDi
2
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Induced drag penalty- Elastic wing
Near elliptic distribution
Design (1)
Optimal wing Off-design (2)
Optimal wing Off-design (2)
Non-optimal wing Scenario I
Off-design (2) Non-optimal wing
Scenario II Lift coefficient,
LC
)1(
LC = 0.60
)2(
LC = 0.42
)2(
LC = 0.42
)2(
LC = 0.42
Span efficiency, e )1(
maxe = 0.99736
)2(
maxe = 0.99884
)2(e = 0.98912
)2(e = 0.97922
Induced drag
coefficient, iD
C
0.01539
0.00749
0.00758
0.00766
Induced drag penalty,
)2(max
)2()2(max
e
ee
0.01
0.02
~2 drag count (0.0002)
ARe
CC LDi
2
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Induced drag penalty- Elastic wing Near elliptic distribution
0
0.1
0.2
0.3
0.4
0.5
0.6
0 0.2 0.4 0.6 0.8 1
eta
span
load
optimal
Scenario II
Scenario I
0
1
2
3
4
5
6
0 0.2 0.4 0.6 0.8 1eta
ang
le o
f in
cid
ence
optimal
Scenario II
Scenario I
Spanload Total angle of incidence
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Induced drag penalty- Rigid wing
Straight-line wrapped surfaces
Design condition (1)
Optimal wing Off-design condition (2)
Non-optimal wing Off-design condition (2)
Optimal wing Lift coefficient,
LC
)1(LC = 0.6 )2(
LC = 0.42 )2(LC = 0.42
Altitude,
h
)1(h = 43000 ft )2(h = 35000 ft )2(h = 35000 ft
Span efficiency, e )1(maxe = 0.99722 )2(e = 0.98937 )2(
Cost penalty – Scenario INear elliptic distribution
Consider induced drag about 25% of total drag, then 0.25x0.01= 0.25% penalty on total drag
16.65 liter/km, then loss 16.65x0.0025= 0.04 liter/km
Max range 15000, cruise about 5000 km loss 200 liter/flight
Assume 300 flights/year, half flown at a lower altitude than the design altitude
30000 liter/year fuel loss
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Two types of total angle of incidence distributions investigated at off-design condition at a lower lift coefficient than design lift coefficient.
For near elliptic spanload (near optimal wing with respect to induced drag) such changes resulted in about a two drag-count increase which may be sufficient to suggest tailoring the structure as the flight condition changes
The straight-line wrapped surfaces was found more effective at the off-design conditions if the wing was not tailored because it was insensitive to the structural deformation and the penalty level was lower.
Concluding Remarks
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Work in progress
Study complete flight envelope, ascend, cruise and descend Optimize the wing structure so that the deformation provides near
optimal wing twist associated with the changing flight condition. Composite wing skin and treat fiber orientation(s) as design