NASA LogoNTRSNTRS - NASA Technical Reports ServerSearchmore_vertCollectionsAboutNewsHelpLogin Back to ResultsAerodynamic Coefficients from Aeroballistic Range Testing of Deployed- and Stowed-SIAD SFDT ModelsThis report documents a ballistic-range test campaign conducted in 2012 in order to estimate the aerodynamic stability characteristics of two configurations of the Supersonic Flight Dynamics Test (SFDT) vehicle prior to its initial flight in 2014. The SFDT vehicle was a test bed for demonstrating several new aerodynamic decelerator technologies then being developed under the Low-Density Supersonic Decelerator (LDSD) Project. Of particular interest here is the Supersonic Inflatable Aerodynamic Decelerator (SIAD), an inflatable attached torus used to increase the drag surface area of an entry vehicle during the supersonic portion of the entry trajectory. Two model configurations were tested in the ballistic range: one representing the SFDT vehicle prior to deployment of the SIAD, and the other representing the nominal shape with the SIAD inflated. Both models were fabricated from solid metal, and therefore, the effects of the flexibility of the inflatable decelerator were not considered. The test conditions were chosen to match, as close as possible, the Mach number, Reynolds number, and motion dynamics expected for the SFDT vehicle in flight, both with the SIAD stowed and deployed. For SFDT models with the SIAD stowed, 12 shots were performed covering a Mach number range of 3.2 to 3.7. For models representing the deployed SIAD, 37 shots were performed over a Mach number range of 2.0 to 3.8. Pitch oscillation amplitudes covered a range from 0.7 to 20.6 degrees RMS. Portions of this report (data analysis approach, aerodynamic modeling, and resulting aerodynamic coefficients) were originally published as an internal LDSD Project report [1] in 2012. In addition, this report provides a description of the test design approach, the test facility, and experimental procedures. Estimated non-linear aerodynamic coefficients, including pitch damping, for both model configurations are reported, and the shot-by-shot trajectory measurements, plotted in comparison with calculated trajectories based on the derived non-linear aerodynamic coefficients, are provided as appendices. Since the completion of these tests, two full-scale SFDT flights have been successfully conducted: one in June 2014 [2, 3], and one in June 2015 [3].Document ID20170011507Acquisition SourceAmes Research CenterDocument TypeTechnical Memorandum (TM)AuthorsWilder, Michael C.*(NASA Ames Research Center Moffett Field, CA, United States)*Brown, Jeffrey D.*(Engineering Research and Consulting, Inc. Moffett Field, CA, United States)*Bogdanoff, David W.*(Engineering Research and Consulting, Inc. Moffett Field, CA, United States)*Yates, Leslie A.*(Aerospace Computing, Inc. Mountain View, CA, United States)*Dyakonov, Artem A.*(NASA Langley Research Center Hampton, VA, United States)*Clark, Ian G.*(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)*Grinstead, Jay H.*(NASA Ames Research Center Moffett Field, CA, United States)*Date AcquiredDecember 5, 2017Publication DateNovember 1, 2017Subject CategoryAerodynamicsReport/Patent NumberARC-E-DAA-TN47243NASA/TM-2017-219693Funding Number(s)CONTRACT_GRANT: NNN12AA01CCONTRACT_GRANT: NNA10DE12CCONTRACT_GRANT: NNA15BB15CDistribution LimitsPublicCopyrightPublic Use Permitted.KeywordsGround TestBallistic RangEntry VehicleAerodynamicsAvailable DownloadsNameType20170011507.pdfSTIcloud_downloadcontent_copyvisibilityRelated RecordsThere are no records associated with this record.visibility_offNo Preview Available
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