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Experimental and Computational Sonic Boom Assessment of Lockheed-Martin N+2 Low Boom ModelsFlight at speeds greater than the speed of sound is not permitted over land, primarily because of the noise and structural damage caused by sonic boom pressure waves of supersonic aircraft. Mitigation of sonic boom is a key focus area of the High Speed Project under NASA's Fundamental Aeronautics Program. The project is focusing on technologies to enable future civilian aircraft to fly efficiently with reduced sonic boom, engine and aircraft noise, and emissions. A major objective of the project is to improve both computational and experimental capabilities for design of low-boom, high-efficiency aircraft. NASA and industry partners are developing improved wind tunnel testing techniques and new pressure instrumentation to measure the weak sonic boom pressure signatures of modern vehicle concepts. In parallel, computational methods are being developed to provide rapid design and analysis of supersonic aircraft with improved meshing techniques that provide efficient, robust, and accurate on- and off-body pressures at several body lengths from vehicles with very low sonic boom overpressures. The maturity of these critical parallel efforts is necessary before low-boom flight can be demonstrated and commercial supersonic flight can be realized.
Document ID
20150012177
Acquisition Source
Ames Research Center
Document Type
Technical Publication (TP)
Authors
Cliff, Susan E.
(NASA Ames Research Center Moffett Field, CA, United States)
Durston, Donald A.
(NASA Ames Research Center Moffett Field, CA, United States)
Elmiligui, Alaa A.
(NASA Langley Research Center Hampton, VA, United States)
Walker, Eric L.
(NASA Langley Research Center Hampton, VA, United States)
Carter, Melissa B.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
July 1, 2015
Publication Date
January 1, 2015
Subject Category
Research And Support Facilities (Air)
Aircraft Design, Testing And Performance
Aerodynamics
Fluid Mechanics And Thermodynamics
Report/Patent Number
ARC-E-DAA-TN20758
NASA/TP-2015-218483
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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