Document
NASA-CR-195183 v
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High Lift Aerodynamics
School of Aeronautics and
Astronautics
Purdue University
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John Sullivan
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Steve Schneider
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Graduate Student
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- Bryan Campbell k-
u.; .J E I UnderGraduate Students t.
- Greg Bucci
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- Rod Boone (Shaw University)
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- Shad Torgerson
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- Rick Erausquin
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- Chad Knauer
High Lift Aerodynamics
School of Aeronautics and
Astronautics
Purdue University
John Sullivan
Steve Schneider
Graduate Student
- Bryan Campbell
UnderGraduate Students
- Greg Bucci
- Rod Boone (Shaw University)
- Shad Torgerson
- Rick Erausquin
- Chad Knauer
• Sponsored by NASA AMES
- Project Monitor- Larry Erickson
- $30,000
High Lift Aerodynamics
School of Aeronautics and
Astronautics
Purdue University
John Sullivan
Steve Schneider
Graduate Student
- Bryan Campbell
UnderGraduate Students
- Greg Bucci
- Rod Boone (Shaw University)
- Shad Torgerson
- Rick Erausquin
- Chad Knauer
Impact of High Lift on
Aircraft Performance
• For a 150 Passenger Transport
Aircraft
- A 5% increase in Take-off L/D
,, 15% increase in Payload, or,
,> 11% increase in Range
A
5% increase in Max. Lift at Landing
,, 20% increase in Range
,, 3 Knot Decrease in Approach Speed
• Goal
- Design of Optimum High Lift Systems
with Minimum Complexity
Objective of Current
Program
• Experimental Program Aimed at
Providing a Physical Picture of the
Flow Physics and Quantitative
Turbulence Data of the Interaction of
a High Reynolds Number Wake with a
Flap Element
• Coordinate with Researchers
Developing Computational
Procedures
- Stuart Rogers- NASA Ames
- Kyle Anderson/Russ Rausch- NASA Langley
- Mark Drela - MIT
• Coordinate with NASA Ames
Experiments
- Joe Marvin/George Meteer
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Instrumentation
• Pitot Probe, 5 Hole Probe
• Hot Wire Anemometry
- 1, 2, 3 Component
• LDV
- 1, 2 Component
PIV
• Flow Visualization
- Laser Sheet, Strobe Light
Design of the High Lift
Experiment
• 2-D
- X-Foil
- MCARFA
• 3-D
- PMARC
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Figure 2(b): NACA 4415 - XFOIL pressure distributions
Re = 0.5 x 10'x6
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..... alpha = 0 ..... alpha = 2 --. alpha=5 -o.... alpha = 7 -- -alpha=10 -o alpha= 12 -,_-- alpha= 15 0.2 0.4 0.6 0.8 1.0 1.2 1.4 1.6 1.8 2.0 0.21 ..... ...... ..... ]..... . ...... ...... : ..... ..... ;..... ......
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Re = 0.5 x 10/'6
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Facilities
• 1/4 Scale ( To Investigate 3-D effects)
- Tunnel Cross-Section (1 ft. x 1.5 ft.)
- Flat Plate - L= 8 ft.
- Flap Chord - c= 1.2 ft.
- Reynolds Number Range (based on L)
,_ Re = .5 to 6.0 Million
Full Scale
- Tunnel Cross-Section (4 ft. x 6 ft.)
- Flat Plate - L = 24 ft.
- Flap Chord - c = 5 ft.
- Reynolds Number Range( based on L)
_ Re = 2.0 to 45.0 Million
1/4 Scale Facility
Results
Pitot Probe Surveys
PIV
Survey at tunnel middle - Vinf=60 fps, 10" from t.e. (182 pts) !
v >, I I I 20 i i 2 4 6 8 10 Distance from Duct Bottom (in.)
Fig. 4: Wake Survey (No Flap) 3D Wake Survey - 1/4 scale, Vinf=-60 fps, 10" from t.e, Fig. 5: Wake Survey (No Flap) (Io/26/g3) Wake Survey with Flap Deflected 25 deg (probe aligned with freestreom dirsction) Survey at x=2" Survey at x=4" 55 : I : w : w : I : 55
50 ............................... i .............. 5o
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45 ........... ; ..... ; ....._ ..... ' .... "..... ": .... _ 45 40 ........................... ' ....." .:.... _ 40 25 25 20 20 -4 -2 0 2 4 6 8 -4 -2 0 2 4 6 8 Distance from Duct Bottom (in.) Distance from Duct Bottom (in.)
Survey at x=9" Survey at x=6"
55, : , : , : , : , 55 : I : I : I : I : I : /
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Distance from Duct Bottom (in.)
Wake Survey with Flop Deflected 25 deg (lo/26/93)
(probe aligned with freestreom dirsction) Survey eL x=12" Survey at x=14" 50 ....\__...,_:.- 50 .....
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Distance from Duct Bottom (in.)
Survey at x=16" : 't : I : I : I : ! : , . • : • :
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Full Scale Facility
• Status
- Construction Complete
,, Foam-Fiberglass with Smooth Gel-Coat
- Pitot Probe Surveys
- Flow Visualization
12/I 2/03
Mean Velocity Profile in Wake
(With roof on lest section) 60- o l v o ............ • ................... ° ...................
55- • = i g g o 50 .................... ...... . ...... • ...... q ............ • .....
o i o i w • i q • • ° ,w .... • ...... • .....
o 40 "" ..
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I1) 30- = (SLlrvey at:l.5 ft) = • z ...... o...... • ..... P -o ............ r .....
25- w l • i i • l l • i i • v | • g l m l 20 i i i i i i i -20 -16 -12 -8 -4 0 4 8 12 16 Vertical Distance from Flap Pivot (in.)
(0.25" between data points)
Mean Velocity Profile in Wake
(With roof on test sedion) ou , , .
.......,......i...... :...... ,......i...... , ......,............
! I g _ w | i w i w r • q i i | i v i w w i • v , v i _ i i e • _u .................................................. - ............
_v • • w v I w w m • ! • • u o I i w i _ J I ! J i _ w i i • o • I • 45 .................................................
w i w o • _ i ! u m i i _ • _ o w w • v i w i o 40 ................. " ...... • ......
t i i • ! = = 0 w t w i 35 ' ": .'
n," 30 ..... : : : i_ u g o ii i i • ' ' e r3 ' ' '
_urveyat_ft) i. i :: /
25 ...............................................................
20 ........
-20 -16 -12 -8 A 0 4 8 12 16 Vertical Distance from Flap Pivot Point (in.)
Mean Velocity Profile in Wake
(With roof on test section) 6O i t e w Q o * * i i v i i i i • i ....... , ...... • ...... - ..... • ..... • "* ° * " ............ r .....
5O t i | (n • * i a v ...... • ....... • ...... o ...... _ ..... • .....
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w w O o = , v > • w • = e • i r- ! i ' e (SUrvey a1'.4.5 fl) : : '.
e o ; o .................. • =" ........ * - - - - 9- --- - ° * ...... ._ ...... g. - • - - • • i * • t I i • * o o t o • i * t J i * ( , v w i i I I I I I I I - -20 -16 -12 -8 -4 0 4 8 12 16 Vertical Distance from Flap Pivot (in.)
(0.25" between data points) 1 2/! at0
Mean Velocity Profile in Wake (AOA=0 deg)
65 - (Corner floor in place) g i , 60 ....... . ....... : ..... , .......... : i . , • , 0 • _ ....... u. ° . J ...... I. ...... J .................. • ..... t.." ....
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Vertical Distance from Flap Pivot (in.)
(0.25" between data points) 12119193
Mean Velocity Profile in Wake (AOA=10 deg)
(Corner floor in place)
6O
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Vertical Distance from Flap Pivot (in.)
(0.25" between data points)
Conclusions
• 1/4 Scale Facility
- Pitot Probe and PIV Data
- Small 3-D Effects Up to Flap Stall
• Full Scale Facility
- Operational
- Preliminary Pitot Probe Data
Recommendations
• Experiments in Full Scale Facility
- Work with Turbulence Modelers and CFD
People to Develop Design Capability of
High Lift Systems of High Reynolds
Numbers
• Issues
- Wake Structure
- Wake Bursting
- Coves
- Trailing Edge Treatment
° Facility Improvements
- Blowing in Flap/Side Wall Corner
,, Higher Lift on Flap with 2-D Flow