Overview of NASA Efforts (related to SWBLI research) An overview of NASA's restructured ARMD Program and the resulting new projects. Areas of research pertaining to shock wave boundary layer interaction are highlighted. Plans and status for specific tasks are presented

Long-Davis, Mary Jo

NASA Technical Reports Server

1Overview of NASA GRC’s Efforts In SWBLI
10th Annual SWBLI Technical Interchange Meeting 
Mary	Jo	Long-Davis
NASA	Glenn	Research	Center
Chief,	Inlets	and	Nozzles	Branch
May	10-11,	2017
https://ntrs.nasa.gov/search.jsp?R=20170009568 2019-08-31T01:50:38+00:00Z
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NASA
Aeronautics Research
• NASA Aeronautics Research Mission 
Directorate Programs and Projects
• NASA Glenn High Speed Inlet Technology
• Stream-traced External Compression Inlet 
(STEX)
• Quiet SuperSonic Technology (QueSST) 
model test in 8’x6’ SWT
• NASA Glenn SWBLI CFD Activities 
• NASA Glenn SWBLI Validation Experiment
Outline
3
NASA
Aeronautics Research
NASA Aeronautics Research Six Strategic Thrusts
Safe, Efficient Growth in Global Operations
• Enable full NextGen and develop technologies to substantially
reduce aircraft safety risks
Innovation in Commercial Supersonic Aircraft
• Achieve a low-boom standard
Ultra-Efficient Commercial Vehicles
• Pioneer technologies for big leaps in efficiency and 
environmental performance
Transition to Low-Carbon Propulsion
• Characterize drop-in alternative fuels and pioneer 
low-carbon propulsion technology
Real-Time System-Wide Safety Assurance
• Develop an integrated prototype of a real-time safety 
monitoring and assurance system
Assured Autonomy for Aviation Transformation
• Develop high impact aviation autonomy applications
4
NASA
Aeronautics Research
Aeronautics Research Mission Directorate
Advanced	Air	
Transport	Technology
Project	(AATT)
Advanced	Air	
Vehicles	(AAVP)
Airspace	Operations
And	Safety	(AOSP)
Integrated	Aviation	
Systems	(IASP)
NASA Aeronautics Program Structure
Transformative	Aeronautics
Concepts	(TACP)
Revolutionary	Vertical
Lift	Technology	Project
(RVLT)
Commercial	Supersonic
Technology	Project
(CST)
Hypersonic	Technology
Project	(HT)
Advanced	Composites
Project	(AC)
Airspace	Technology
Demonstrations	Project
(ATD)
SMART	NAS	– Testbed
for	Safe	Trajectory
Operations	Project
Safe	Autonomous
System	Operations	Project
(SASO)
UAS	Integration
in	the	NAS	Project
Flight	Demonstration
and	Capabilities	Project
(FDC)
Leading	Edge
Aeronautics	Research
for	NASA	Project
(LEARN)
Transformative	Tools
and	Technologies	Project
(T3)
Convergent	Aeronautics
Solutions	Project
(CAS)
--------------------------- Mission	Programs	-------------------------------------- Seedling	Program
Effective FY17
Aeronautics	Evaluation
and	Test	Capabilities
Project	(AETC)
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NASA
Aeronautics Research
What is the Advanced Air Vehicles Program (AAVP)?
Continues much 
of the research that was in the 
Fundamental Aeronautics Program, 
with a new focus on research that is 
directly related to the newly defined 
strategic thrusts. It now houses the 
Advanced Composites Project that 
was previously in the Integrated 
Systems Research Program. It also 
includes the ground test portion 
of the former Aeronautics 
Test Program.
Conducts fundamental research 
to improve aircraft performance and 
minimize environmental impacts
from subsonic air vehicles
Develops and validates tools, technologies 
and concepts to overcome key barriers, including 
noise, efficiency, and safety for vertical lift vehicles
Explores theoretical research for potential advanced 
capabilities and configurations for low boom 
supersonic aircraft. 
Conducts research to reduce the timeline for 
certification of composite structures for aviation
Ensures the strategic availability, accessibility, 
and capability of a critical suite of aeronautics 
ground test facilities to meet Agency and 
national aeronautics testing needs. 
Advanced 
Air Vehicles 
Program
The Fundamental Aeronautics Program, ground test capabilities, atmospheric environments related safety.
Projects
Advanced Air Transport 
Technology
Revolutionary Vertical 
Lift Technology
Commercial Supersonics 
Technology
Hypersonic Technology
Advanced Composites
Aeronautics Evaluation 
and Test Capabilities
6
NASA
Aeronautics Research
What is the Transformative Aeronautics Concepts (TAC) 
Program?
Solicits and encourages 
revolutionary concepts
Creates the environment 
for researchers to become 
immersed in trying out 
new ideas
Performs ground and 
small-scale flight tests
Drives rapid turnover 
into new concepts
Cultivates multi-disciplinary, 
revolutionary concepts to enable 
aviation transformation and harnesses 
convergence in aeronautics and non-
aeronautics technologies to create new 
opportunities in aviation
Knocks down technical barriers and infuses 
internally and externally originated concepts 
into all six strategic thrusts identified by 
ARMD, creating innovation 
for tomorrow in the aviation system. 
Provides flexibility for innovators to 
explore technology feasibility and 
provide the knowledge base for 
radical transformation. 
Transformative 
Aeronautics 
Concept 
Program
While mission programs focus on solving challenges, this program focuses on cultivating opportunities.
Projects
Leading	Edge	Aeronautics	Research	for	
NASA
Transformational	Tools	&	Technologies
Convergent	Aeronautics	Solutions
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NASA
Aeronautics Research
• NASA Aeronautics Research Mission 
Directorate Programs and Projects
• NASA Glenn High Speed Inlet Technology
• Stream-traced External Compression Inlet 
(STEX)
• Quiet SuperSonic Technology (QueSST) 
model test in 8’x6’ SWT
• NASA Glenn SWBLI CFD Activities 
• NASA Glenn SWBLI Validation Experiment
Outline
8
NASA
Aeronautics Research
Proposed 8x6 SWT Test of Inward-Turning Low-Boom Inlet
NASA Inlet            Adapter                       Cold-Pipe                   Mass Flow Plug
STATUS
• Continuing to work STEX design at off-design 
conditions
• LTO conditions ( 0.1 <  M < 0.3), including aux 
inlets , angle of attack, angle of sideslip
• Paper on off-design performance to be 
presented at ISABE in Sept 2017.
• The AIP adapter (11.75” diffuser exit diam to 
16” cold pipe/mass flow plug) is finished and 
will be shipped to the 8x6 for storage. 
• Validation test article mech design complete; 
structural analysis underway. Preparing for fab 
estimate and build decision. Sketch of proposed 8x6 Inlet Test Rig
-Commercial Supersonic Technologies (CST) Project POC: Chuck Trefny and John Slater (GRC)
PROBLEM
Demonstrate the performance and operability of an inward-turning, high-
performance, low-boom inlet with acceptable distortion levels to enable 
integration with a turbine engine.
OBJECTIVES OF PROPOSED 8x6 SWT TEST
(1) Validate the effects of bleed and other boundary layer control schemes (e.g., 
vortex generators) on overall inlet performance, 
(2) Provide better understanding of non-linear sub-critical phenomena, 
(3) Determine tolerance to angles of attack and yaw 
(4) Determine off-design Mach number performance
APPROACH
Perform mechanical design, fabrication and GRC 8x6 Supersonic Wind Tunnel 
test of an inlet model.  The model hardware will include using existing inlet 
adapter, cold-pipe, and mass flow plug.  Existing adapter requires addition of 
rakes and hub to serve as Aerodynamic Interface Plane (AIP).
9
NASA
Aeronautics Research
• NASA Aeronautics Research Mission 
Directorate Programs and Projects
• NASA Glenn High Speed Inlet Technology
• Stream-traced External Compression Inlet 
(STEX)
• Quiet SuperSonic Technology (QueSST) 
model test in 8’x6’ SWT
• NASA Glenn SWBLI CFD Activities 
• NASA Glenn SWBLI Validation Experiment
Outline
10
NASA
Aeronautics Research
Quiet SuperSonic Transport (QueSST) Test
8x6-Foot Supersonic Wind Tunnel
OBJECTIVE:  To verify the 
aerodynamic performance 
predictions of the fuselage 
shape, control surfaces and 
engine inlet using a 9%-
scale wind tunnel model of 
a low-boom vehicle design
POCs: Ray Castner, John Slater, Vance Dippold, David 
Friedlander, Chuck Trefny, Chris Heath, Jon Seidel (GRC)
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NASA
Aeronautics Research
Test Objectives
• The Quiet Supersonic Technology (QueSST) test series will occur in two 
phases:
– Aerodynamic
• Will test a live balance installed to collect differential stability data on various 
control surface configurations and inlet flow-through nacelle screens.
– Propulsion
• Will test with a varied inlet and nozzle in order to collect inlet performance 
information.
• Collect Background Oriented Schlieren (BOS) around inlet areas if 
possible and schedule permits.
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NASA
Aeronautics Research
Model Hardware
Aero Configuration
• Sting	mounted	with	6-
component	live	balance
• Spike	extends	5.1-in	from	nose
• 8	change-able	control	surfaces
• Total	model	length,	nose	(no	
spike)	to	tail:	
– 106.5-in
• Total	wing	span:	
– 33.6-in
• Total	length	nose	(no	spike)	to	
strut	LE:	
– 174.7-in
• Test	Section	Station	(nose,	no	
spike):	
– TS	145.3
• Total	configurations:	
– 53	minor
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NASA
Aeronautics Research
Model Hardware
Propulsion Configuration
1
• Blade-to-sting	mounted	with	NO	
balance
• Aft	geometry	changed
– No	tails/stabilizers
• Total	model	length,	nose	(no	
spike)	to	MFP	mixing	can:	
– 124.7-in
• Total	wing	span:	
– 33.6-in
• Total	length	nose	(no	spike)	to	
strut	LE:	
– 174.7-in
• Test	Section	Station	(nose,	no	
spike):	
– TS	145.3
• Total	configurations:	
– 6	minor
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NASA
Aeronautics Research
Model Hardware
Propulsion Configuration
• Linear actuation of 
plug via electric motor
• AIP diameter: 3-in
• MFP diameter: 3-in
• Total MFP travel: 2.8-
in
• Ejector only needed 
when MFP pressure 
ratio is less than 2.0
• Ejector requirements:
– 100-psig 
compressed air
– 0.9-lbm/sec
• Ejector supply from 
450-psig air system
1
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NASA
Aeronautics Research
Test Matrix
Propulsion Configuration
1
• Mach 0.30 – 1.6 (nom)
• Varying factors:
– Inlets
• Design
• Alternate (fat lip)
– Vortex Generators
• Baseline
• Alternate 1
• Alternate 2
• Off
Note: primary source of propulsion data
Note: sample test matrix for a single propulsion configuration.
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NASA
Aeronautics Research
Propulsion Airframe Integration CFD
Potential need for additional validation data and CFD tool refinements
• NASA analysis of C607.1 design was 
performed:
– Large differences (>5%) in NASA FUN3D 
vs. LM CFD++ inlet recovery and 
distortion.
– Differences attributed to predicted flow-
field on top of vehicle.
• At GRC, the QueSST project marks the first 
time full vehicle aerodynamic analysis was 
performed using FUN3D on a mature vehicle 
design. 
• The QueSST aircraft is unique in that it 
contains an aft-fuselage, top-mounted inlet 
installation, with complex shock-wave 
boundary-layer interactions that are sensitive to 
geometry and difficult to predict.
• Depending on the success of this first test, 
more investment/validation data sets likely 
needed to bring PAI best practices up to the 
same maturity level as sonic boom analysis.
92% Recovery
Fun3D
97% Recovery
CFD++
Cruise Pt, 
Mach 1.42, AOA 1.7
Boundary Layer 
Growth and Shock-
Induced Separation
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NASA
Aeronautics Research
Study of VGs on the QueSST Inlet (C606)
Objectives:
• Vortex generators in current design are used to sweep the 
boundary layer away from inlet.
• NASA explored smaller vortex generators (VGs) aft of the 
cockpit to reduce drag and shocks generated by the VGs.
• Examine effect of design factors (height, length, angle).
Approach:
• Use Wind-US CFD code with vortex generator model.
• Simplified aircraft for structured grid to focus on VGs.
• Consider effect on boundary layer at inlet entrance.
Results/Significance:
• Study showed smaller VGs can effectively be used 
to sweep the boundary layer away from the inlet.
• Alternate VG designs were shared with Lockheed 
for consideration in future configuration updates.
Inlet Lip
VG h75
Configuration
VG Location
18
NASA
Aeronautics Research
• NASA Aeronautics Research Mission 
Directorate Programs and Projects
• NASA Glenn High Speed Inlet Technology
• Stream-traced External Compression Inlet 
(STEX)
• Quiet SuperSonic Technology (QueSST) 
model test in 8’x6’ SWT
• NASA Glenn SWBLI CFD Activities 
• NASA Glenn SWBLI Validation Experiment
Outline
19
NASA
Aeronautics Research
Transformational Tools & Technologies Project
Level 2 Milestone Completion
Milestone:
Evaluate advanced RANS and 
scale resolving simulations 
capability for prediction of shock-
boundary layer interactions.
Exit Criteria:
Quantify improvement in 
shock induced separation 
length and associated 
improvements in prediction of 
Reynolds stresses.
Due Date:
03/31/2017
SWTBLI	Focus	region
UFAST M2.25 SWBLI
30deg Axi Compression Corner 
Transonic Diffuser
POCs: Nick Georgiadis, Julie Dudek, Manan Vyas 
and Jim DeBonis (GRC)
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NASA
Aeronautics Research
• The effect of the shear stress limiter in the Shear Stress Transport (SST) 
model was examined for shock separated flows
– Experimental data was used to characterize shear stress behavior
– The SST model was adjusted to better replicate the experimental findings
– Improved shock boundary layer predictions were obtained with the modified SST model
• Reynolds stress models (SSG/LRR & Wilcox) were evaluated for transonic 
diffuser and supersonic compression corner flows 
– Provide enhanced physics and potential for more accurate predictions in some flows 
(physical representation of turbulence intensities)
– RSMs were very sensitive to the numerical scheme
– RSMs did not show significant benefit boundary layer separation prediction
– Need for additional research and include Algebraic Reynolds Stress models
• LES was used to simulate the UFAST shock boundary layer interaction
– Digital filtering turbulent inflow generation created accurate boundary layer profiles upstream 
of the shock
– Separation is greatly under-predicted
– Several areas are being investigated including numerical schemes, grid etc.
Summary of GRC SWBLI CFD Activities
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NASA
Aeronautics Research
Investigation of Shear Stress Limiter
• The Menter Shear Stress Transport (SST) model is possibly the most widely 
RANS used turbulence model for aerospace flows.  It is a k-w model with 
“shear stress transport” part of the model coming from the limiter:
• The Menter BSL model is very similar to SST, but with no limiter.
• Shear stress limiter sets a1 = 0.31 = -u’v’/k, using observations of Bradshaw, 
Townsend, & others -- for zero pressure gradient and mild adverse gradient 
flows.
• Experimental data (UFAST, Smits et al, others) shows -u’v’/k exceeds 0.31 in 
SWTBLI flows.  This quantity is known as the “structure parameter.”
• Others (Wilcox, Tan and Jin, Edwards) also have investigated values for a1
greater than 0.31.
• This work:
1. A range of a1 from 0.31 to 0.40 was investigated, for several cases 
including SWTBLIs.  (Larger values for a1 are very similar to BSL)
2. Examined details of experimental turbulent measurements alongside 
computations to determine appropriate value(s) for a1 in SWTBLI 
flows.
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NASA
Aeronautics Research
UFAST SWBLI Test Case 
2010 AIAA SWTBLI Workshop
• Mach	2.25	flow	approaching	SWTBLI	region.
• Several	RANS	and	LES	(including	hybrid	RANS-LES)	solutions	submitted;	
most	widely	used	RANS	turbulence	models	were	SST	and	SA.
SWTBLI	Focus	region
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NASA
Aeronautics Research
UFAST Results when varying “a1”
Experiment Menter SST	k-w
Menter BSL	k-w Menter SST	k-w, a1 =	0.355
• BSL and SST models provide solutions on either side of experimental data for 
SWTBLIs.
• For all flows, but especially SWTBLIs, increasing a1 results in less limiting of 
turbulent shear stress…..smaller separations.
• a1 = 0.355 is recommended value for SWTBLI problems.
• The capability to vary a1 was added to Wind-US version 4.  The most recent 
Wilcox k-w also uses a larger effective value for a1=0.343.
24
NASA
Aeronautics Research
• NASA Aeronautics Research Mission 
Directorate Programs and Projects
• NASA Glenn High Speed Inlet Technology
• Stream-traced External Compression Inlet 
(STEX)
• Quiet SuperSonic Technology (QueSST) 
model test in 8’x6’ SWT
• NASA Glenn SWBLI CFD Activities 
• NASA Glenn SWBLI Validation Experiment
Outline
25
NASA
Aeronautics Research
Turbulence	CFD	Validation	Experiments	(TCFDVE)
POC:	David	O.	Davis	(GRC)		
17cm Axisymmetric Supersonic Wind Tunnel
PROBLEM
Very few Shock Wave/Boundary-Layer Interaction (SWBLI) experiments reported in the open literature meet the rigorous criteria required 
to be considered as a CFD validation dataset. This is particularly true for experiments with detailed turbulence measurements.
OBJECTIVES
Obtain mean and turbulence quantities through a M=2.5 SWBLI of sufficient quantity and quality to be considered as a CFD validation 
dataset. Initial efforts will focus on a Mach 2.5 2-D (in the mean) interaction with follow-on efforts investigating 3-D interactions. Both 
attached and separated interactions will be considered.
APPROACH
A new M=2.5 17cm axisymmetric facility has been constructed to investigate SWBLIs. The facility is located in Test Cell W6B at NASA 
GRC. The SWBLI is generated by a cone-cylinder located on the centerline of the facility. The strength of the interaction is varied by 
changing the cone angle. The measurement region of interest is where the conical shock interacts with the naturally occurring facility 
boundary-layer that is highlighted by the box shown in Figure 1. The new facility will be instrumented with conventional pressure 
instrumentation as well as hot-wire anemometry for measurement of turbulence quantities. Non-intrusive optical techniques such as PIV 
will be incorporated in the future. Test are also planned with dynamic surface shear film and fast response Pressure Sensitive Paint (PSP) 
in collaboration with Innovative Scientific Solutions, Incorporated (ISSI).
RESULTS
Normal hot-wire measurements have been 
completed. 
SIGNIFICANCE
The data to be generated has been 
previously unavailable. Further, 
development of an in-house capability to 
investigate SWBLIs will allow CFD code 
developers and turbulence modelers to 
have direct input into the experiment. It will 
also allow the ability to revisit 
measurements if deemed necessary.
-Transformational Tools & Technologies (T3) Project
26
NASA
Aeronautics Research Your Title Here


Overview of NASA GRC's Efforts In SWBLI

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