laminar-to-turbulent transition in hypersonic bl with
TRANSCRIPT
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Laminar-to-Turbulent Transition in
Hypersonic BL with Spanwise
Inhomogeneity
Roger Kimmel
Principal Engineer
Aerospace Systems Directorate
Air Force Research Laboratory
16 July 2015
Distribution A: Approved for public release, distribution is unlimited. 24 June 2015, 88ABW-2015-3223
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2
Overview
• Introduction
– Focus on BLT with significant spanwise nonuniformity
– Examine limits of applicability for PSE
• HIFiRE-5
– IR and Kulite measurements in Purdue
• Cone at AoA
– Stability calculations
– Re-examination of Stetson high-Reynolds Mach 6 data
• HIFiRE-1, 5a analysis
• Test capability development
– Ludwieg tube
– FLDI
– Krypton PLIF
16 October 2015
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Push to Complex Configurations
16 October 2015
HIFiRE-5
Li 2012
Kimmel 1995
DARPA / AF Falcon HTV-2
Advanced Hypersonic
Weapon
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Flows With Strong Spanwise
Nonuniformity
16 October 2015
HIFiRE-5 Gosse
(2009) Elliptic Cone
Huntley (2000)
HIFiRE-5
Paredes (2014)
What are limits of applicability
for PSE in complex flows?
When do non-modal
instabilities become
important?
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Approach / Benefits
• Generate flowfields with spanwise nonuniformity
• Measure stability characteristics and compare to
PSE, search for regions where PSE may be
inadequate
• Benefits – increased confidence with PSE, improved
vehicle design
16 October 2015
Borg – HIFiRE-5
Crossflow
development
Jewell – Cone at AoA
Instability growth with
varying spanwise
nonuniformity
Tufts – PSE
Modal instabilities
in 3D flows
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Last Year’s Results
• HIFiRE-5
– Measured fluctuating surface pressures in TAMU ACE wind tunnel
– Mach 6 results similar to Purdue noisy, but lower amplitude
– Strong effect of Mach number and tunnel conditions on observed instabilities
• HIFiRE-1 high AoA transition
– 2nd mode observed on cone at AoA in tunnel
– Indented transition front observed in flight, not in ground test
– Wind tunnel transition at AoA biased to lower Reynolds compared to flight, but not as much as a=0
– Nosetip steps probably not contributor to this
• Additional results (not briefed)
– Leading-edge trip on HIFiRE-5 flight correlated with Redk
– Refined AoA & heating for HIFiRE-5 flight
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HIFiRE-5 IR Transition Measurements
16 October 2015
Quiet, Re=12.3x106/m
Borg (AFRL), Purdue M=6 Quiet Tunnel
Steel forebody,
PEEK frustum
IR successful, Kulites do not significantly influence results
Flow
Instrumented Blank
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Stationary Cross Flow Instability Growth
16 October 2015 Quantitative stationary crossflow measurement may be possible
Borg (AFRL), Purdue M=6 Quiet Tunnel
x=305.1 mm
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Traveling Cross Flow Instability Growth
16 October 2015
Re=6.6x106/m Re=8.9x106/m
Re=9.9x106/m Re=12.8x106/m
Spatial growth observable
Borg (AFRL), Purdue M=6 Quiet Tunnel
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Comparison With PSE
16 October 2015
Re=8.3x106/m
Re=8.9x106/m
LST/LPSE agree well with data at lower Reynolds
Lakebrink (Boeing), Borg (AFRL)
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PSE Analysis - 8-deg M=6 Blunt Cone
Experiment
16 October 2015
Jewell (AFRL, NRC)
Small radius - high N-factors, ~7
Drop in N-factor when transition occurs within swallowing region
(similar to Marineaux)
1983 AF High-Reynolds M=6 tests
Effect of entropy-swallowing on transition
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M=6 High-Reynolds Amplication Rates
16 October 2015
Jewell (AFRL, NRC)
- Second-mode freqs push PCB capabilities
- FLDI in works
2% bluntness
Re=20x106/ft
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HIFiRE-1 SBLI
16 October 2015
Prabhu (NASA), Kimmel (AFRL)
Wind tunnel results useful for
calibrating turbulence models for
flight SBLI
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HIFiRE-5 Heat Transfer Analysis
16 October 2015
f=0 f=90
t=20 sec t=32 sec
Miller, Kimmel (AFRL), Jewell (AFRL,
NRC)
Transverse
conduction
explains heating
discrepancies
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HIFiRE-5 Pressure Measurements for
Flight Attitude
16 October 2015 Surface pressures suitable for attitude determination
Miller, Kimmel (AFRL), Jewell (AFRL, NRC)
AoA (deg)
Yaw
(d
eg
)
Ao
A (
de
g)
Ya
w (
de
g)
Min
% R
MS
Devia
tio
n
Time, sec
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Summary
• HIFiRE-5 stability
– New IR transition measurement capability
– Traveling cross flow coexists with stationary
– Traveling detectable before stationary
– Before breakdown, phase speed and wave angle predicted
well with LPSE
• Cone at AoA / bluntness analysis
– Correlating N-factor drops when Retr drops
• HIFiRE flight analysis
– Tunnel - calibrated Reynolds stress model works well for
flight SBLI
– HIFiRE-5 pressure instrumentation as FADS works well
16 October 2015
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Upcoming Work
16 October 2015
• IR calibration and stationary/traveling crossflow analysis (Borg) –
further insight into crossflow development
• Cone stability at AoA and bluntness effects (Jewell) – effect of strong
spanwise nonuniformity on instability development
• FLDI (Jewell, Lam) – measure freestream and boundary layer
instabilities
• Freestream disturbance / shock interaction (Duan, UMR) –
receptivity, tunnel characterization
• Ludwieg Tube characterization
• Pate correlation (Juliano) –wind tunnel noise scaling
• LASTRAC/PSE3D analysis for 3D flows (Tufts) – provide LPSE
analysis for HIFiRE-5 and cone at AoA
• Krypton LIF (Narayanaswamy, Lam, Carter) – boundary layer imaging
• HIFiRE-5b – refly scheduled November 2015
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Upcoming Work
16 October 2015
Andor iXON
EMCCD
Camera
AutoTracker III with
Prism Harmonic
Separator
Lumonics HD-
300
Dye Laser
GCR-170 Nd:YAGSpherical convex lens
Laser Sheet, = 214.7 nm
=355 nm
= 532 nm
= 544 nm
AT-III
Cylindrical concave lens
Narayanaswamy,
Lam, Carter – Kr
LIF
Ludwieg Tube - commissioning
Jewell – Cone at AoA
Jewell, Lam - FLDI
High-Reynolds M=6 tunnel,
Ludwieg tube
Medtherm
PCB
Bench setup
Shock tube checkout
High-Reynolds Mach 6,
Ludwieg tube
Correlation measurements
Bench demo in jet
Ludwieg tube demo
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Technical Challenges
• Amplitude-based transition prediction
– Atmospheric disturbance measurement
– Surface quality prediction
– Wind tunnel disturbance measurement
• Bluntness transition mechanisms
– Implications for transition control (If you mediate one transition mechanism, what pops up next to replace it?)
– Implications for transition prediction (Do we clearly know where our methods are applicable and inapplicable?)
16 October 2015
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Acknowledgments
• Steve Schneider, Purdue
• Cam Carter, James Miller, Ben Hagen, AFRL
16 October 2015
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BACKUP
16 October 2015
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Publications
16 October 2015
Borg, M. P., Kimmel, R. L., Hofferth, J., Bowersox, R. D. W. and Mai, C. L. N., “Freestream Effects on Boundary
Layer Disturbances for HIFiRE-5,” AIAA 2015-0278, January 2015.
Kimmel, R. L., Prabhu, D., “HIFiRE-1 Turbulent Shock Boundary Layer Interaction –Flight Data and
Computations,” AIAA paper 2015-xxxx, June 2015.
Jewell, J. S., Miller, J. H., Kimmel, R. L., “Correlation of HIFiRE-5 Flight Data With Computed Pressure and Heat
Transfer,” AIAA paper 2015-xxxx, June 2015.
Kimmel, R.L., Adamczak, D., Paull, A., Paull, R., Shannon, J., Pietsch, R., Frost, M., and Alesi, H., “HIFiRE-1
Ascent Phase Boundary Layer Transition,” AIAA Journal of Spacecraft and Rockets, vol. 52, no. 1, January-February
2015.
Stanfield, S. A., Kimmel, R. L., Adamczak, D., and Juliano, T. J., “Boundary-Layer Transition Experiment During
Reentry of HIFiRE-1,” AIAA Journal of Spacecraft and Rockets, vol. 52, no. 3, May-June 2015, pp. 637-649.
Juliano, T. J., Adamczak, D. A., and Kimmel, R. L., “HIFiRE-5 Flight Test Results,” AIAA Journal of Spacecraft
and Rockets, vol. 52, no. 3, May-June 2015, pp. 650-663.
Borg, M. P., Kimmel, R. L., and Stanfield, S., “Traveling Crossflow Instability for the HIFiRE-5 Elliptic Cone,”
AIAA Journal of Spacecraft and Rockets, vol. 52, no. 3, May-June 2015, pp 664-673.
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Business Update
16 October 2015
• Budget (7/13/2015)
• Total authority - $375,000
• Obligated - $286,423
• Unobligated - $88,577
• Full-time personnel
• Dr. Matthew Borg – AFRL/RQHF
• Dr. Joseph Jewell – NRC postdoc
• Dr. Brian Lam – Spectral Energies
• Dr. Matthew Tufts – OAI postdoc
• Summer personnel
• Dr. Thomas Juliano – Notre Dame (SFFP)
• Christopher Huffman – Notre Dame (SFFP)
• Dr. Lian Duan – University Missouri-Rolla
• Dr. Venkateswaran Narayanaswamy – NC State
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FLDI Cross-Correlation Measurements
16 October 2015
Jewell (AFRL, NRC), Lam (AFRL, Spectral Energies), Parziale (Stevens)
FLDI phase velocity measurements feasible