Shaped Sonic Boom Demonstration SSBD

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Shaped Sonic Boom Demonstration (SSBD)
Program Overview
Joseph W. Pawlowski SSBD/SSBE Project Manager No
rthrop Grumman Corporation
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QSP Phase I II System Studies
FOR PUBLIC RELEASE
Phase I (CY 00/01)
Phase II (CY 02/03)
Concept Study
System Validation
Focused On Strike Concept
Global Strike Missionized Vehicle
Dual Relevant QSP Concept
Business Jet Missionized Vehicle

• Key Activities
• Definitive CONEMP Study
• Detailed Vehicle Subsystem Definition
• Six Wind Tunnel Tests
• High Fidelity CFD
• Adv. Composite Manufacturing Demo
• F-5 Shaped Sonic Boom Flight Test

Key Technologies
Low Boom Shaping Joined Wing Top-Mounted Inlet
Laminar Aero
Synthetic Vision Adv. Sandwich Composite Synthet
ic Vision
Adaptive Cycle Engine
FOR PUBLIC RELEASE
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Sonic Boom Generation, Propagation and Aging
FOR PUBLIC RELEASE
FOR PUBLIC RELEASE
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SSBD Program Objective
FOR PUBLIC RELEASE

• To Provide the First Ever In-Flight Demonstration
  of an Aircraft that Produces a Shaped Sonic Boom
  that Persists Through the Real Atmosphere to the
  Ground

20 ms
70 ms
Employs Aircraft Shaping Techniques First
Proposed by Dr. Seabass and Dr. George in the
1960s
FOR PUBLIC RELEASE
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Why the F-5E?
FOR PUBLIC RELEASE

• Aircraft Configuration Is Very Amenable to the
  Type of Forebody Modifications Required to
  Produce a Shaped Boom Signature
  
• Long Nose, Blended Canopy, and Inlets Relatively
  Far Back
  
• Very High Overall Fineness Ratio (9.7)
• Lightweight
• Modification Is Relatively Low Risk Due to
• Similarity with F-5 Family of Aircraft
• Extensive Database of Modified Forebodies with
• Comprehensive Wind Tunnel and Flight Testing
• Cost-Effective Test Approach
• Limited Wind Tunnel Testing and Computational
• Fluid Dynamics (CFD) Analysis Required for F-5
  Mod
  
• Low Aircraft Operating Cost
• Supersonic Performance Capability with Margin
• Maximum Mach Number of 1.64 at 36,000 ft

FOR PUBLIC RELEASE
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SSBD Major Challenges
FOR PUBLIC RELEASE

• Using a Surrogate Aircraft to Produce a Shaped
  Sonic Boom Signature Presents Significant
  Challenges
  
• Must Minimize Impact to Existing Aircraft to
  Maximize ROI for Cost-Effective Approach
  
• Vehicle Mod Cannot Compromise Safety-of-Flight or
  Adversely Affect Handling Qualities and
  Performance
  
• Need to Compensate for Existing Vehicle
  Characteristics Which Are Not Practical to
  Modify
  
• Inlet Location and Spillage Shock Effects
• Wing Configuration / Shock Effects
• Key Design Constraints
• Shall Not Extend Forward of F-5F Nose
• Maintain Fuselage Width Forward of Inlets
• No Interference with Main Gear Doors

Proposal Concept
FOR PUBLIC RELEASE
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FOR PUBLIC RELEASE
Overall Concept of Operations

• Define F-5E Shape Modifications Required to Meet
  SSBD Goals and Reach Technical Consensus with
  SSBD Working Group
  
• Conduct Inlet Spillage Shock Measurement Test
  with Basic F-5E
  
• Conduct Sonic Boom Test in Supersonic Wind Tunnel
  to Validate Computational Fluid Dynamics (CFD)
  Predictions
  
• Conduct High and Low Speed Safety-of-Flight Wind
  Tunnel Tests
  
• Install SSBD Modifications and Instrumentation
  onto Basic F-5E
  
• Obtain NAVAIR Flight Clearance / Conduct First
  Flight Readiness Review
  
• Conduct Testing to Clear Flight Envelope for SSBD
  Tests
  
• Configure EAFB Test Range with Sonic Boom
  Detector Arrays
  
• Fly Baseline Navy F-5E Over Test Range, Followed
  by F-5SSBD
  
• Collect and Analyze Sonic Boom Data for Both
  F-5s
  
• Present Results to Validate Theory of Shaped Boom
  Persistence

FOR PUBLIC RELEASE
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FOR PUBLIC RELEASE
Comparison of Near-Field Signatures
FOR PUBLIC RELEASE
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SSBD Technical Solution
FOR PUBLIC RELEASE
Predicted Pressure Signature Behavior
as it Propagates from Aircraft to Ground
Predicted Ground Signature With Atmospheric Smoot
hing
FOR PUBLIC RELEASE
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FOR PUBLIC RELEASE
F-5SSBD Aircraft Configuration
FOR PUBLIC RELEASE
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Modification Overview
FOR PUBLIC RELEASE

• Remove Nose Section Forward of F.S.137.50
• Remove Radar and Its Associated Equipment Remove
  Guns
  
• Deactivate Speed Brakes
• Relocate Flight Essential Equipment in Nose to
  Gun Bays
  
• Install SSBD Nose Which Ties into FS 137.5
  Bulkhead
  
• Install Segmented Lower Fairing Aft of FS 137.50
• Integrate New NG Doors into SSBD Lower Fairing
• Relocate ECS Vents to Aft End of Fairing
• Relocate UHF Antenna and Total Temp Probe
• Install Flight Test Equipment in Gun Bay and
  Cockpit

FOR PUBLIC RELEASE
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Build-Up Approach To Development Validation
FOR PUBLIC RELEASE
Boom Tunnel Tests
Extensive CFD
Inlet Shock Flight Test
NASA Dryden Feb 02
NASA Glenn Mar May 02
Mod Shape Defined Jan 02
Correlations Completed
SC Tunnel Test
Force Tunnel Test
NGC LSWT Aug 02
AEDC 4T Oct 02
Pre-FRR - 1/03
IDRs - 12/01 2/02
PDR - 3/02
CDR - 7/02
FOR PUBLIC RELEASE
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Fabrication Flight Operations
FOR PUBLIC RELEASE
Mod Nose Attached
USN F-5E Arrives NGSA
Fairings Attached
Jan 03
Mar 03
Apr 03
Pre-Flight Prep
First Taxi
First Flight
May 03
9 Jun 03
24 Jul O3
Envelope Expansion Ferry Flights
Back-to-Back Probe Flights
17 Flawless FlightsOver 1 Month!
FOR PUBLIC RELEASE
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Back-to-Back Data Flight27 August 2003
FOR PUBLIC RELEASE
(45 Second Separation Between Aircraft During
Supersonic Run)
NAS Fallon VFC-13 F-5E and F-5 SSBD at Palmdale,
CA
F-5 SSBD Takes Off at Dawn Enroute to EAFB Super
sonic Corridor
F-5 Pilots
Roy Martin CDR Darryl Spike Long L
CDR Dwight Tricky Dick
FOR PUBLIC RELEASE
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SSBD Flight Path
FOR PUBLIC RELEASE
FOR PUBLIC RELEASE
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First-Ever Shaped Sonic Boom Recorded 27 August
2003
FOR PUBLIC RELEASE
Signatures recorded during SSBD back-to-back data
flights in the Edwards AFB supersonic flight
corridor early morning Estimated conditions M
ach 1.36, Altitude 32,000 ft
FOR PUBLIC RELEASE
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SSBD Program Status
FOR PUBLIC RELEASE

• DARPA/NASA Extremely Satisfied with Test Results
• Dr. Wlezien These are about as unambiguous
  results as you can get.
  
• Peter Coen We were all blown away by the
  clarity of what we measured.
  
• Program Success Has Been Featured on TV, Radio,
• Internet and in Numerous Newspaper and
  Magazines
  
• Test Results Presented at National /
  International Venues
  
• National Press Club Washington, D.C.
• World Aviation Congress Meeting Montreal,
  Canada
  
• Best of Whats New in 2003 in Popular Science
  Magazine
  
• Multiple Requests Received for Papers and
  Presentations
  
• Awarded NASA Contract for Follow-On Program

NASA Photo
NASA Photo
FOR PUBLIC RELEASE
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Shaped Sonic Boom Experiment (SSBE)
Program Overview
Shaped Sonic Boom Experiment
Joseph W. Pawlowski SSBD/SSBE Project Manager No
rthrop Grumman Corporation
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Test Background/Objectives
FOR PUBLIC RELEASE
Shaped Sonic Boom Experiment
Based on the Success of the DARPA SSBD Program,
NASA Created a Follow-On Program to Further
Explore the Characteristics and Robustness of
Shaped Sonic Booms Using the F-5 SSBD Test
Aircraft

• Up to 21 Test Flights Planned
• Achieve M1.4, 32k ft. Design Condition
• Collect Data at Off-Design Conditions
• Collect Back-to-Back Data with Navy F-5E
• Collect Near-Field Probing Data with NASA F-15
• Collect Data Above Ground Turbulence Layer with
  USAF TPS Glider
  
• Attempt to Record Focused Boom

FOR PUBLIC RELEASE
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Revised Ground Track
FOR PUBLIC RELEASE
Shaped Sonic Boom Experiment
FOR PUBLIC RELEASE
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FOR PUBLIC RELEASE
SSBE Test Summary
Shaped Sonic Boom Experiment

• Met or Exceeded All Flight Test Goals
• 21 Test Flights Conducted January 1222, 2004
• 1 Functional Check Flight
• 8 F-5 SSBD Solo Flights
• 8 F-5 SSBD / F-5E Back-to-Back Flights
• 4 F-5 SSBD / F-15B Probing Flights
• Repeatable Data Collected Between M1.35 and
  M1.45
  
• Well Over 1300 Sonic Boom Signatures Recorded by
  Ground Sensor Array at EAFB North Base
  
• USAF TPS Glider Obtained Excellent Data Above
  Ground Turbulence Layer on 14 Flights
  
• 45 Near-Field Probing Measurements Obtained with
  F-15
  
• Successfully Recorded Focused Boom on 2 Flights
• Excellent Weather for Meaningful Data Collection
  Experienced Throughout Test Phase
  

FOR PUBLIC RELEASE
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Initial SSBE Flight Test Results
FOR PUBLIC RELEASE
Shaped Sonic Boom Experiment
F-15B Probe Data
Glider Data
Ground Data
FOR PUBLIC RELEASE
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SSBD/SSBE Program Summary
FOR PUBLIC RELEASE
Shaped Sonic Boom Experiment

• Shaped Sonic Boom Persistence Theory was Proven
  in Actual Flight Conditions
  
• Sonic Boom Intensity Can Be Reduced Through
  Aircraft Shaping
  
• Ground Boom Signature for a Supersonic Aircraft
  Can Be Predicted
  
• DARPA and NASA Were Delighted with the Quantity
  and Quality of the Supersonic Data
  
• Mapped Shockwave Propagation Around the
  Near-Field of SSBD Aircraft, at the Mid-Field
  Using a Glider, and at the Ground Level in
  Various Atmospheric Conditions
• Recorded Boom Focus Data Using ¼ G Pushover
• Program Data Will be Invaluable to Future
  Supersonic Aircraft Designs Allows Designers to
  Go Forward with Confidence in Ability to Predict
  Boom Signatures

FOR PUBLIC RELEASE
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SSBD/SSBE Test and Support Team