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EAD, National Aerospace Laborotories, Bangalore
S.B.Verma
CSIR-NAL
AR&DB Annual Symposium, 13-14 May 2011
Shock Wave Boundary-Layer Interaction Study on a 20o
Compression Corner Using PSP and Kulites
Principal Investigator
S.B.Verma
Co-investigatorChanna Raju and Manisankar, C.
Council of Scientific and Industrial Research (CSIR),
Experimental Aerodynamics Division, National Aerospace Laboratories
Bangalore 560 017
AR&DB Sanction Ref : AR&DB Project DARO/08/1031316/M/IAR& DB Project No. : 1316
Date of Commencement : July 29th, 2009
Original PDC : June, 2011
Project Cost : Rs.8.999 Lakhs
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EAD, National Aerospace Laborotories, Bangalore
S.B.Verma
CSIR-NAL
AR&DB Annual Symposium, 13-14 May 2011
Introduction
ramp flows
forebody ramp flows
axial corner
(glancing shock)shock reflection
crossing-shock
interaction
Typical Vehicle Components where SWBLI is Expected
Wind tunnel experiments are indispensable, especially
to investigate pressure loads, shock unsteadiness characteristics in regions
of interest and to look for the mechanisms responsible
to obtain the desired design information with sufficient reliability
neck region
interaction point (I)
separation
compression fan
sonic line
undisturbed
boundary-layer
Xphysep
LsepL
reattachment
compression fan
separated
shear layer
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EAD, National Aerospace Laborotories, Bangalore
S.B.Verma
CSIR-NAL
AR&DB Annual Symposium, 13-14 May 2011
Specific Objectives of the Proposal
To gain a broad understanding of the shock-wave boundary layer interaction
(SWBLI) phenomena on a 20ocompression corner with emphasis on shock
unsteadiness and the related surface-flow structure development at freestream
Mach number of 2.0.
To compare the SWBLI characteristics on the ramp by varying the boundary-
layer thickness () and using one vortex-generator configuration
To obtain surface pressure map of such interactions using PSP to get better
insight of the global mean-flow characteristics
Surface oil visualization to study surface flow characteristics and Spark Schlieren
visualization for the different test cases.
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EAD, National Aerospace Laborotories, Bangalore
S.B.Verma
CSIR-NAL
AR&DB Annual Symposium, 13-14 May 2011
Actual Model Mounted in the 0.3m Tunnel
For Pressure measurements and schlieren Moundel mounting for PSP
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EAD, National Aerospace Laborotories, Bangalore
S.B.Verma
CSIR-NAL
AR&DB Annual Symposium, 13-14 May 2011
boundary-layer tripramp
flat plate
leading edge plate
strut
sting support
model support strut
schlieren window
base plate
Compression Corner Model
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S.B.Verma
CSIR-NAL
AR&DB Annual Symposium, 13-14 May 2011
10 Kulite transducer
Locations (XT-140M)
10m
m5m
m
5m
m
VG
strip
5m
m
Kulite XCQ-93 6nos.
(a) VG1
(a) VG2
Mechanical Vortex Generators
3
10o
3.5
3.5
10o
4
X
Z
Y
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8/21EAD, National Aerospace Laborotories, Bangalore
S.B.Verma
CSIR-NAL
AR&DB Annual Symposium, 13-14 May 2011
separation shock
reattachment shock
trip initiated shocks
tripped blayer
reattached
blayer
With trip; no VG
separation shock
reattachment shock
trip initiated shocks
shocks from VGs
reattached
blayer
With trip; VG1
separation shock
reattachment shock
trip initiated shocks
shocks from VGs
reattached
blayer
With trip; VG2
With trip; noVG
With trip; VG1
With trip; VG2
Spark Schlieren Pictures
=1.6mm; 27.5 =3.85mm; 12.5
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S.B.Verma
CSIR-NAL
AR&DB Annual Symposium, 13-14 May 2011
Spark Schlieren Movies
no VG VG1
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S.B.Verma
CSIR-NAL
AR&DB Annual Symposium, 13-14 May 2011
(a) no VG
separation line
reattachment line
(b) VG1
corrugated
separation linevortex trails
reattachment line
(c) VG2
corrugated
separation line
vortex trails
striation patternreattachment line
Surface Oil Visualization: h/= 0.65
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S.B.Verma
CSIR-NAL
AR&DB Annual Symposium, 13-14 May 2011
vortex trails
corrugated
separation line
vortex trails
corrugated
separation line
Surface Oil Visualization: h/= 0.26
VG1 VG2
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S.B.Verma
CSIR-NAL
AR&DB Annual Symposium, 13-14 May 2011
Schematic of the Surface Flow Development
Overall surface flow pattern
X
Z
Y
corrugated shock
micro-ramps
streamwise
CRVs
main flow
reverse flow
flow
reverse flowcorrugated
separation line
Corrugated separation line pattern
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13/21EAD, National Aerospace Laborotories, Bangalore
S.B.Verma
CSIR-NAL
AR&DB Annual Symposium, 13-14 May 2011
Streamwise Mean Pressure and rmsDistribution
X/L
Pw
/P
0.7 0.8 0.9 1 1.1 1.20
1
2
3
4
no VG
VG1
VG2
(a)
(d)
X/L
w
/P
w
0.6 0.7 0.8 0.9 1 1.1 1.20
0.02
0.04
0.06
0.08
0.1
no VG
VG1
VG2
(d)
base plate ramp section
corner location
(c)
X/L
w
0.6 0.7 0.8 0.9 1 1.1 1.20
1
2
3
4
no VG
VG1
VG2
(c)
base plate ramp section
corner location
h/=0.65 h/=0.26
(b)
X/L
w
/P
w
0.7 0.8 0.9 1 1.1 1.20
0.02
0.04
0.06
0.08
0.1
no VG
VG1
VG2
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S.B.Verma
CSIR-NAL
AR&DB Annual Symposium, 13-14 May 2011
Spectral Analysis
frequency (Hz)
G(f)(p
si2/Hz)
100
101
102
103
104
10510
-10
10-8
10-6
10-4
10-2
100
no VG
VG1
VG2
(a)X/L= 0.951
Separation region (1)
frequency (Hz)
G(f)(psi
2/Hz)
100
101
102
103
104
10510
-10
10-8
10-6
10-4
10
-2
100
no VG
VG1
VG2
(c)X/L= 1.017
reattachment region (3)
frequency (Hz)
G(f)(p
si2/Hz)
100
101
102
103
104
10510
-10
10-8
10-6
10-4
10-2
100
no VG
VG1
VG2
(b)X/L= 0.97
Separated region (2)
frequency (Hz)
G(f)(psi
2/Hz)
100
101
102
103
104
10510
-10
10-8
10-6
10-4
10
-2
100
no VG
VG1
VG2
(d)X/L= 1.089
Downstream of reattachment (4)
1
23 4
X/L
w/P
w
0.7 0.8 0.9 1 1.1 1.20
0.02
0.04
0.06
0.08
0.1
no VG
VG1
VG2
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S.B.Verma
CSIR-NAL
AR&DB Annual Symposium, 13-14 May 2011
X (mm)
Pw
/P
200 220 240 260 280 300 3200.5
1
1.5
2
2.5
3
transducer - no VG
PSP - no VG
Y (mm)
Cp
-0.2 -0.1 0 0.1 0.20
0.1
0.2
(b)
Y (mm)
Cp
-0.2 -0.1 0 0.1 0.20
0.1
0.2
(c)
X (mm)
Pw
/P
240 250 260 270 2800.5
1
1.5
2
PSP - no VG
PSP - VG1
PSP - VG2
(a)
PSP Measurements
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17/21EAD, National Aerospace Laborotories, Bangalore
S.B.Verma
CSIR-NAL
AR&DB Annual Symposium, 13-14 May 2011
time (ms)
Rpp
(0,0,
)
0 0.3 0.6 0.9 1.2 1.50
0.2
0.4
0.6
0.8
1
1.2
0.912
0.931
0.951
0.971
1.017
1.035
(a)
time (ms)
Rpp
(0,0,
)
0 0.3 0.6 0.9 1.2 1.50
0.2
0.4
0.6
0.8
1
1.20.892
0.912
0.931
0.951
0.971
1.017
1.035
(b)
time (ms)
Rpp
(0,0,
)
0 0.3 0.6 0.9 1.2 1.50
0.2
0.4
0.6
0.8
1
1.20.912
0.931
0.951
0.971
1.017
1.035
(c)
Auto correlation Measurements
no VG VG1 VG2
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EAD, National Aerospace Laborotories, Bangalore
S.B.Verma
CSIR-NAL
AR&DB Annual Symposium, 13-14 May 2011
Cross - correlation Measurements
(a)
time (ms)
Rpp
(,0,
)
-2 -1.5 -1 -0.5 0 0.5 1 1.5 2-0.2
-0.1
0
0.1
0.2
0.3
0.4
0.5
0.6
0.912 0.931
0.912 0.951
0.931 0.951
0.951 0.971
time (ms)
Rpp
(,0,
)
-2 -1.5 -1 -0.5 0 0.5 1 1.5 2-0.2
-0.1
0
0.1
0.2
0.3
0.4
0.5
0.60.892 0.912
0.912 0.951
0.931 0.9510.951 0.971
(b)
time (ms)
Rpp
(,0,
)
-2 -1.5 -1 -0.5 0 0.5 1 1.5 2-0.2
-0.1
0
0.1
0.2
0.3
0.4
0.5
0.60.912 0.931
0.912 0.951
0.931 0.951
0.951 0.971
(c)
no VG VG1 VG2
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EAD, National Aerospace Laborotories, Bangalore
S.B.Verma
CSIR-NAL
AR&DB Annual Symposium, 13-14 May 2011
Conclusions
Control devices generate streamwise vortices that dramatically modify the overall
flow structure development in the entire interaction region.
A well-defined separation line (with no control) gets replaced by a highly corrugated
separation line (with control).
A well defined reattachment line gets replaced by a striation pattern (with control)
In the intermittent region of separation, a significant reduction in peak rmsvalue (by
33%) for VG1 followed by VG2 (by 44%) occurs
VG1 configuration shows favorable flow control in both axial locations and hence, seems
to be a better flow control VG configuration
The comparison between the pressure port data and PSP is generally good
The spanwise wall pressure variation shows a sinusoidal pattern indicating trails of
vortices generated from the VG configurations
Flow control helps reduce the fluctuations of the separation shock and hence, alleviate
the fluctuating pressure loads
Suggestions for future work:Effect of micro-ramps need to be studied in both subsonic and supersonic flows
Other flow control devices such as air-jet vortex generators (skew angle) need to be investigated
Application of these devices to other SWBLIs such as swept fin, blunt fin etc. needs to be tested
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EAD, National Aerospace Laborotories, Bangalore
S.B.Verma
CSIR-NAL
AR&DB Annual Symposium, 13-14 May 2011
Statement of Account
Period Costs released (under
different heads)
Expenditure incurred
(under different heads)
upto 30.04.2011
Balance as on
30.04.11 (under
different heads)
(Rs in lakhs) (Rs in lakhs) (Rs in lakhs)
2009-11 Capital Equipment
3.90
3.90 0.00
Research staff2.16
2.16 0.00
TA/DA0.45
0.45 0.00
Consumables1.25
1.25 0.00
Contingencies0.40
0.40 0.00
Overheads
0.839
0.839 0.00
Total 8.999 8.999 0.00
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EAD National Aerospace Laborotories Bangalore
S.B.Verma
CSIR NAL
AR&DB Annual Symposium, 13-14 May 2011
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