Computational Fluid Dynamics Validation of a Single, Central Nozzle Supersonic Retropropulsion Configuration

Cordell, Christopher E., Jr.

Title:

Computational Fluid Dynamics Validation of a Single, Central Nozzle Supersonic Retropropulsion Configuration

dc.contributor.advisor	Braun, Robert D.
dc.contributor.author	Cordell, Christopher E., Jr.
dc.contributor.corporatename	Georgia Institute of Technology. School of Aerospace Engineering
dc.contributor.corporatename	Georgia Institute of Technology. Space Systems Design Lab
dc.date.accessioned	2011-02-16T21:55:14Z
dc.date.available	2011-02-16T21:55:14Z
dc.date.issued	2009-05
dc.description	AE8900 MS Special Problems Report	en_US
dc.description.abstract	Supersonic retropropulsion provides an option that can potentially enhance drag characteristics of high mass entry, descent, and landing systems. Preliminary flow field and vehicle aerodynamic characteristics have been found in wind tunnel experiments; however, these only cover specific vehicle configurations and freestream conditions. In order to generate useful aerodynamic data that can be used in a trajectory simulation, a quicker method of determining vehicle aerodynamics is required to model supersonic retropropulsion effects. Using computational fluid dynamics, flow solutions can be determined which yield the desired aerodynamic information. The flow field generated in a supersonic retropropulsion scenario is complex, which increases the difficulty of generating an accurate computational solution. By validating the computational solutions against available wind tunnel data, the confidence in accurately capturing the flow field is increased, and methods to reduce the time required to generate a solution can be determined. Fun3D, a computational fluid dynamics code developed at NASA Langley Research Center, is capable of modeling the flow field structure and vehicle aerodynamics seen in previous wind tunnel experiments. Axial locations of the jet terminal shock, stagnation point, and bow shock show the same trends which were found in the wind tunnel, and the surface pressure distribution and drag coefficient are also consistent with available data. The flow solution is dependent on the computational grid used, where a grid which is too coarse does not resolve all of the flow features correctly. Refining the grid will increase the fidelity of the solution; however, the calculations will take longer if there are more cells in the computational grid.	en_US
dc.identifier.uri	http://hdl.handle.net/1853/36936
dc.language.iso	en_US	en_US
dc.publisher	Georgia Institute of Technology	en_US
dc.rights	Unless otherwise noted, all materials are protected under U.S. Copyright Law and all rights are reserved
dc.rights.metadata	https://creativecommons.org/publicdomain/zero/1.0/
dc.rights.uri	https://rightsstatements.org/page/InC/1.0/?language=en
dc.subject	Computational fluid dynamics	en_US
dc.subject	Entry, Descent, and Landing (EDL)	en_US
dc.subject	Supersonic retropropulsion	en_US
dc.title	Computational Fluid Dynamics Validation of a Single, Central Nozzle Supersonic Retropropulsion Configuration	en_US
dc.type	Text
dc.type.genre	Masters Project
dspace.entity.type	Publication
local.contributor.corporatename	Space Systems Design Laboratory (SSDL)
local.contributor.corporatename	Daniel Guggenheim School of Aerospace Engineering
local.contributor.corporatename	Daniel Guggenheim School of Aerospace Engineering
local.relation.ispartofseries	Master's Projects
local.relation.ispartofseries	Master of Science in Aerospace Engineering
relation.isOrgUnitOfPublication	dc68da3d-4cfe-4508-a4b0-35ba8de923fb
relation.isOrgUnitOfPublication	a348b767-ea7e-4789-af1f-1f1d5925fb65
relation.isOrgUnitOfPublication	a348b767-ea7e-4789-af1f-1f1d5925fb65
relation.isSeriesOfPublication	09b1c264-93da-4a60-8e57-4eecff715bc6
relation.isSeriesOfPublication	09844fbb-b7d9-45e2-95de-849e434a6abc