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Wind Tunnel Flow Field Visualizations of the Space Launch System Vehicle AscentA wind tunnel test was conducted to characterize the aeroacoustic environment of several configurations of the Space Launch System during ascent. The test was conducted in the 11-by-11 foot transonic and 9-by-7 foot supersonic test sections at NASA Ames research center. Throughout this experiment data was collected from several types of instrumentation including: dynamic and steady-state pressure sensors, unsteady and steady pressure sensitive paint, time-resolved shadowgraph and infrared imaging. The following details results and analysis from the time-resolved shadowgraph and infrared imaging data systems. The time-resolved shadowgraph provided a qualitative measurement of the near-field turbulent fluctuations. These results helped provide context to the relative magnitude and frequency content of the fluid-structure-interaction driving the surface pressure phenomena characterized by the discrete pressure transducers and unsteady pressure sensitive paint. The infrared imaging was used to verify boundary layer trip effectiveness and provide temperature correction for the unsteady pressure sensitive paint.
Document ID
20190002270
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Garbeff, Theodore J., II
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
April 11, 2019
Publication Date
January 7, 2019
Subject Category
Launch Vehicles And Launch Operations
Aerodynamics
Report/Patent Number
ARC-E-DAA-TN57211
Meeting Information
Meeting: AIAA SciTech Forum 2019
Location: San Diego, CA
Country: United States
Start Date: January 7, 2019
End Date: January 11, 2019
Sponsors: American Institute of Aeronautics and Astronautics (AIAA)
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
Shadowgraph
Image processing
Flow Visualization
Space Launch System
Infrared imaging
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