DLR.de • Folie 1
> EXPERIMENTAL RESULTS ON SHOCK-WAVE/BOUNDARY-LAYER INTERACTION > Daub, Willems, Gülhan • 4.3.2015
EXPERIMENTAL RESULTS ON SHOCKWAVE/BOUNDARY-LAYER INTERACTION
INDUCED BY A MOVABLE WEDGE
D. Daub, S. Willems and A. Gülhan
DLR.de • Folie 2
> EXPERIMENTAL RESULTS ON SHOCK-WAVE/BOUNDARY-LAYER INTERACTION > Daub, Willems, Gülhan • 4.3.2015
Shock-Wave/Boundary-Layer Interaction
• Over-expanded nozzles
• Inlets
• Vehicle structure
Touber and Sandham 2009 - Theoretical and Computational Fluid
Dynamics
-> Efficiency and reliability of the vehicle
DLR.de • Folie 3
> EXPERIMENTAL RESULTS ON SHOCK-WAVE/BOUNDARY-LAYER INTERACTION > Daub, Willems, Gülhan • 4.3.2015
Trisonic Wind Tunnel (TMK) at DLR, Cologne
• Mach number range:
0.5 to 4.5
• Up to 5.7 using ejector
and heater
• Variable nozzle contour
• 0.6x0.6 m test section
DLR.de • Folie 4
> EXPERIMENTAL RESULTS ON SHOCK-WAVE/BOUNDARY-LAYER INTERACTION > Daub, Willems, Gülhan • 4.3.2015
Experimental Setup
Wedge
Instrumented test panel
Coupling and bearings
High performance drive
DLR.de • Folie 5
> EXPERIMENTAL RESULTS ON SHOCK-WAVE/BOUNDARY-LAYER INTERACTION > Daub, Willems, Gülhan • 4.3.2015
Test conditions
M
p∞ [kPa]
T∞ [K]
u∞ [m/s]
Re [106/m]
2.5
21.2
126.7
567
37.7
3.0
15.6
97.2
595
49.4
3.5
11.7
83.2
643
55.1
4.0
8.7
64.9
650
70.1
DLR.de • Folie 6
> EXPERIMENTAL RESULTS ON SHOCK-WAVE/BOUNDARY-LAYER INTERACTION > Daub, Willems, Gülhan • 4.3.2015
Instrumentation
• PSI ports for static pressure distribution
• Kulite XCQ-062 pressure transducers
for dynamic pressure (eigenfrequency >
240 kHz)
• National Instruments 24-bit High Speed
Bridge Modules PXIe 4331
• Sampling Rate of 100 kHz
DLR.de • Folie 7
> EXPERIMENTAL RESULTS ON SHOCK-WAVE/BOUNDARY-LAYER INTERACTION > Daub, Willems, Gülhan • 4.3.2015
Boundary-Layer Characterization
• Laser-2-Focus Velocimetry:
Turbulent Intensity of 2%
• Boundary-Layer Profile measured
with miniature pitot rake
DLR.de • Folie 8
> EXPERIMENTAL RESULTS ON SHOCK-WAVE/BOUNDARY-LAYER INTERACTION > Daub, Willems, Gülhan • 4.3.2015
Average Pressure Distribution
M=3
M=4
DLR.de • Folie 9
> EXPERIMENTAL RESULTS ON SHOCK-WAVE/BOUNDARY-LAYER INTERACTION > Daub, Willems, Gülhan • 4.3.2015
PSD: Spatial Distribution
PSD M = 4, 25°
PSD M = 4, 22.5°
DLR.de • Folie 10
> EXPERIMENTAL RESULTS ON SHOCK-WAVE/BOUNDARY-LAYER INTERACTION > Daub, Willems, Gülhan • 4.3.2015
PSD: Spatial Distribution
PSD M=3, 20°
Average pressure distribution
DLR.de • Folie 11
> EXPERIMENTAL RESULTS ON SHOCK-WAVE/BOUNDARY-LAYER INTERACTION > Daub, Willems, Gülhan • 4.3.2015
PSD: Temporal Distribution
PSD M=3, 20°
DLR.de • Folie 12
> EXPERIMENTAL RESULTS ON SHOCK-WAVE/BOUNDARY-LAYER INTERACTION > Daub, Willems, Gülhan • 4.3.2015
PSD: Temporal Distribution
PSD M=3, 20°
DLR.de • Folie 13
> EXPERIMENTAL RESULTS ON SHOCK-WAVE/BOUNDARY-LAYER INTERACTION > Daub, Willems, Gülhan • 4.3.2015
High-Speed Schlieren/Shock Tracking
• Tracking of the separation shock
• Canny edge detection algorithm
• No exact comparison to Kulite
data possible due to 3d effects
near the window
DLR.de • Folie 14
> EXPERIMENTAL RESULTS ON SHOCK-WAVE/BOUNDARY-LAYER INTERACTION > Daub, Willems, Gülhan • 4.3.2015
Fast-Moving Shock
•
•
M = 3.0 & 20°
Schlieren video real time, slowed down by a factor of 100
DLR.de • Folie 15
> EXPERIMENTAL RESULTS ON SHOCK-WAVE/BOUNDARY-LAYER INTERACTION > Daub, Willems, Gülhan • 4.3.2015
Conclusion
• Experiments on Shock-Wave/Boundary-Layer Interaction in the
Trisonic Windtunnel (TMK) at DLR, Cologne
• Flexible setup of variation of the wedge angle
• Data on spatial and temporal distribution of frequencies occurring in
pressure signals in the interaction
Next steps:
• Extensive comparison to new Large Eddy Simulation (LES) of the
Institute of Aerodynamics and Fluid Mechanics at TU München
• Coupling with elastic panel

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