This presentation provides a brief overview of the research underway in the Cruise Efficiency -- Propulsion technical challenge area of NASA's Fundamental Aeronautics Supersonics project. The research involves both computational and experimental efforts in the areas of Advanced Inlet Concepts, High Performance/Wide Operability Fan and Compressors, Advanced Nozzle Concepts and Intelligent Sensors/Actuators. The work consists of both internal NASA research and external efforts funded through the NASA Research Announcement process

DeBonis James R.

NASA Technical Reports Server

Fundamental Aeronautics Program Annual Meeting
New Orleans, Louisiana, October 30 - November 1, 2007
This presentation provides a brief overview of the research underway in the 
Cruise Efficiency – Propulsion technical challenge area of NASA’s 
Fundamental Aeronautics Supersonics project.  The research involves both 
computational and experimental efforts in the areas of Advanced Inlet 
Concepts, High Performance/Wide Operability Fan and Compressors,
Advanced Nozzle Concepts and Intelligent Sensors/Actuators.  The work 
consists of both internal NASA research and external efforts funded through 
the NASA Research Announcement process.
Supersonic Cruise Efficiency - Propulsion
Tech Challenge Overview
Jim DeBonis
NASA Glenn Research Center
Cleveland, OH 44135
216-433-6581
James.R.DeBonis@nasa.gov
https://ntrs.nasa.gov/search.jsp?R=20080005526 2019-08-30T03:07:47+00:00Z
Fundamental Aeronautics Program Annual Meeting
New Orleans, Louisiana, October 30 - November 1, 2007
Supersonic Cruise Efficiency - Propulsion
Tech Challenge Overview
Jim DeBonis
NASA Glenn Research Center
Cleveland, OH 44135
216-433-6581
James.R.DeBonis@nasa.gov
Fundamental Aeronautics Program Annual Meeting
New Orleans, Louisiana, October 30 - November 1, 2007
Motivation
• In order to achieve economic viability, supersonic 
cruise civil aircraft need to achieve unprecedented 
levels of cruise efficiency.  To achieve high efficiency, 
the propulsion system must be designed and 
optimized as an integrated system and installed in an 
optimal way on the airframe.  This cruise efficiency 
must be preserved while 1) meeting stringent airport 
noise requirements at takeoff/landing and 2) 
minimizing  the aircraft’s sonic boom signature.
Fundamental Aeronautics Program Annual Meeting
New Orleans, Louisiana, October 30 - November 1, 2007
Objective
• Develop tools and propulsion technologies that will 
enable the design and analysis of:
– High-efficiency, low-boom, and stable inlets
– High performance/wide operability fans
– High-performance, low-noise low-boom exhaust nozzles
– Intelligent sensors and actuators for variable cycle engines.
Bulk of core turbomachinery work has been 
consolidated under the Subsonic Fixed Wing Project
Fundamental Aeronautics Program Annual Meeting
New Orleans, Louisiana, October 30 - November 1, 2007
Research Elements
• Advanced Inlet Concepts
• High Performance/Wide Operability Fan and 
Compressor
• Advanced Nozzle Concepts
• Intelligent Sensors/Actuators
Fundamental Aeronautics Program Annual Meeting
New Orleans, Louisiana, October 30 - November 1, 2007
Advanced Inlet Concepts
• Supersonic Micro-Array Flow 
Control*
• Assess inlet-fan interactions
– Computational modeling*
– Validation experiment
• Lockheed-Martin inlet
• GRC 12” fan simulator (VIIPAR)
• Supersonic inlet design tools 
and methodologies
– Starting FY08
– Rehabilitate existing 2D codes
– Develop 3D design codes for 
highly integrated inlets
– Quick turnaround performance 
assessments
Micro-ramp flow control device for 
“bleedless” supersonic inlets
Relaxed supersonic compression inlet 
hardware tested in GRC 1’x1’ Supersonic 
Wind Tunnel
* Presentations to follow
Fundamental Aeronautics Program Annual Meeting
New Orleans, Louisiana, October 30 - November 1, 2007
Advanced Inlet Concepts
• Low boom/high performance 
inlet technologies
– Develop highly integrated inlet 
concepts 
– Use the “Icon” Airplane as a 
basis for development
– Utilize new design tools
• Flight Test of Channeled 
Centerbody Inlet
– Patented centerbody design 
allows large throat area 
variation through simple 
lightweight system
– Developed by Techland 
Research under a NASA SBIR
– Will be flight tested under 
supersonics program in FY09 Channeled Centerbody Inlet
Supersonics Project “Icon” Airplane
Fundamental Aeronautics Program Annual Meeting
New Orleans, Louisiana, October 30 - November 1, 2007
• Coupled inlet/fan modeling using 
large-eddy simulation (LES)
– Component analysis - completed
• Isolated Air Force UAV inlet
• Isolated Fan
– Darmstadt Rotor 1
– Both on and off design
– Coupled analysis
• Air Force UAV inlet and 
Honeywell compressor
• To be completed in FY08
– H3D analysis code
• Pressure based
• 3rd order convective terms
• Dynamic Smagorinsky sub-grid 
model
High Performance/Wide Operability
Fan and Compressor
Analysis of U.S. Air Force UAV Inlet
H3D analysis of Darmstadt Rotor 1
Casing static pressure
at off-design condition
measurement calculation
Fundamental Aeronautics Program Annual Meeting
New Orleans, Louisiana, October 30 - November 1, 2007
Advanced Nozzle Concepts
• State of the art nozzle force measurements
– Upgrading NASA’s capabilities for nozzle force measurements
– Simultaneous force and noise measurements
• High Flow Jet Exit Rig in the NASA Glenn Nozzle Acoustic Test Rig 
(NATR)
• Modify, checkout and calibrate existing force balance
• Work will be completed shortly
High Flow Jet Exit Rig, Force Balance and 
Calibration Hardware in NASA Glenn NATR
– 6-component nozzle force 
measurements in supersonic 
wind tunnels
• New task
• Need force and moment 
measurements for highly 
integrated low-boom nozzle 
concepts
• New balance being developed for 
GRC Jet Exit Rig
• Rig used in GRC 9’x15’, 8’x6’ and 
10’x10’ wind tunnels
Fundamental Aeronautics Program Annual Meeting
New Orleans, Louisiana, October 30 - November 1, 2007
Advanced Nozzle Concepts
• Jet plume effects on sonic boom
– New element for FY08
– Assess effect of jet plume on sonic boom
– Develop guidelines for nozzle shape, integration and 
operation for high-performance low-boom operation
– Compliments LANCETS F-15 flight test examining jet plume 
effects on sonic boom
Fundamental Aeronautics Program Annual Meeting
New Orleans, Louisiana, October 30 - November 1, 2007
Intelligent Sensors/Actuators
• Microwave Tip Clearance Sensor
– Use in closed-loop control of 
turbines and variable cycle 
engines
– 5.8GHz Probe developed by 
Radatech/Vibro-meter under SBIR
– Calibrate probe for making tip 
clearance measurements
– Test probes in high pressure 
burner to evaluate performance in 
high temperature environment
• Active Clearance Control
– ACC system demonstrated at 
1140 F (1200 F goal)
– Effective clearance 80% lower 
than industry reference threshold
– Task not continuing due to 
manpower limitations Active Clearance Control Rig at 1140 F
Heater 
Sections
Radiant Heater at Temperature
Microwave Tip Clearance Probe
Fundamental Aeronautics Program Annual Meeting
New Orleans, Louisiana, October 30 - November 1, 2007
NASA Research Announcements (NRAs)
• Round 1 - Awarded Feb. 2007
– “Shock Boundary Layer Interaction Flow Control with Micro-Vortex 
Generators using Large-Eddy Simulation”, Eric Loth, University of 
Illinois
• Round 3 - Recently Selected
– Inlet design and fabrication for a large-scale validation of micro-
ramp flow control device
• Aerodynamic design, mechanical design and fabrication of a supersonic 
inlet model for the purpose of validating micro-array flow control devices
• 2 Awards
– Inlet Bleed Modeling
• Development of a model for porous bleed for use with Computational 
Fluid Dynamics (CFD) simulation of supersonic inlet flows.
• 1 Award
– Flow Angularity Probe 
• Develop a compact, high-response sensor for measurement of 
distortion in subsonic diffuser wind tunnel tests.
• 1 Award
Fundamental Aeronautics Program Annual Meeting
New Orleans, Louisiana, October 30 - November 1, 2007
0
0.2
0.4
0.6
0.8
1
1.2
1.4
0 2 4 6 8 10
u
/
u
∞
y/δref*
LES (MILES)
RANS (SA)
Experiment
H
3.19
Shock Boundary Layer Interaction Flow Control with 
Micro-Vortex Generators using Large-Eddy Simulation
• Develop high-order schemes in a 
production CFD code (Wind) for 
LES of Shock Boundary-Layer 
Interactions
• Examine solution sensitivity to
– numerical scheme
– grid/time-step resolution
• Investigate µ-ramps effect on
– Oblique Shock Boundary Layer 
Interactions (M∞ ca. 2.5)
– Normal Shock Boundary Layer 
Interactions (M∞ ca. 1.4)
– NSBLI Interactions with 
Downstream Diffuser
University of Illinois at Urbana-Champaign
PI: Eric Loth
Fundamental Aeronautics Program Annual Meeting
New Orleans, Louisiana, October 30 - November 1, 2007
Partnerships
• Micro-array flow control for shock-wave boundary-layer 
interactions
– U.S. Air Force Research Laboratory (AFRL), Memorandum of 
Understanding
– Sharing of computational results, experimental data and design of 
experiments methodologies
• Active inlet flow control/high cycle fatigue
– Lockheed-Martin, Space Act Agreement
– L-M provided inlet hardware for testing on GRC fan simulator 
(VIIPAR rig) 
• Testing of the Relaxed Supersonic Compression Inlet
– Gulfstream, Space Act Agreement
– Gulfstream provided inlet hardware for testing in GRC 1’x1’
Supersonic Wind Tunnel
– Shared CFD analysis
Fundamental Aeronautics Program Annual Meeting
New Orleans, Louisiana, October 30 - November 1, 2007
Technical Presentations
"Rapid Calculations of Three-Dimensional 
Inlet / Fan Interaction”
Dr. Rod Chima
NASA Glenn Research Center
"Application of Microramp Flow Control Devices
to an Oblique Shock Interaction”
Ms. Stefanie Hirt
NASA Glenn Research Center


Supersonic Cruise Efficiency - Propulsion Tech Challenge Overview

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