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A Computational Fluid Dynamics Study of Swirling Flow Reduction by Using Anti-Vortex BaffleOBJECTIVES: To evaluate proposed anti-vortex design in suppressing swirling flow during US burn. APPROACH: Include two major body forces in the analysis a)Vehicle acceleration (all three components); b)Vehicle maneuvers (roll, pitch, and yaw). Perform two drainage analyses of Ares I LOX tank using 6 DOF body forces predicted by GN&C analysis (Guidance Navigation and Control) during vehicle ascent: one with baffle, one without baffle. MODEL: Use Ares I defined geometry. O-Grid for easy fitting of baffle. In this preliminary analysis the holes are sealed. Use whole 360 deg. model with no assumption of symmetry or cyclic boundary conditions. Read in 6DOF data vs time from a file.
Document ID
20170001497
Acquisition Source
Marshall Space Flight Center
Document Type
Presentation
Authors
Yang, H. Q.
(Jacobs Engineering and Science Services and Skills Augmentation Group (ESSSA) Huntsville, AL, United States)
West, Jeff
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Peugeot, John W.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
February 9, 2017
Publication Date
January 9, 2017
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
M17-5762
Report Number: M17-5762
Meeting Information
Meeting: AIAA Scitech 2017 Conference
Location: Grapevine, TX
Country: United States
Start Date: January 9, 2017
End Date: January 13, 2017
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NNM12AA41C
Distribution Limits
Public
Copyright
Public Use Permitted.
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