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Space Launch System Aeroacoustic Wind Tunnel Test ResultsCharacterization of accurate launch vehicle unsteady aerodynamics is critical for component and secondary structure vibroacoustic design. For the National Aeronautics and Space Administration (NASA) Space Launch System (SLS), aeroacoustic environments have been derived primarily through sub-scale wind tunnel testing. Both optical techniques and high frequency pressure measurements have been utilized across multiple testing facilities and numerous vehicle configurations to develop a range of preliminary and detailed environments. As the vehicle has matured and evolved, the data collected from each subsequent configuration has allowed for comparison studies which isolate the effects of certain outer mold line (OML) features on measured fluctuating pressure levels. This paper presents observations on some of those effects for features which include abort system protuberances, various fairings geometries, interstage flanges, and multibody interactions between a central core and fall away boosters. These features, and the flow conditions produced by them, are broadly applicable to many launch vehicle configurations.
Document ID
20190000725
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Steva, Thomas B.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Pollard, Victoria J.
(Jacobs Engineering Group, Inc. Huntsville, AL, United States)
Herron, Andrew J.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
February 14, 2019
Publication Date
January 7, 2019
Subject Category
Spacecraft Design, Testing And Performance
Launch Vehicles And Launch Operations
Report/Patent Number
M18-7124
Meeting Information
Meeting: AIAA Science and Technology Forum and Exposition
Location: San Diego, CA
Country: United States
Start Date: January 7, 2019
End Date: January 11, 2019
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Public Use Permitted.
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