Hypersonic wind-tunnel free-flying experiments with onboard instrumentation

Handle URI:
http://hdl.handle.net/10754/563998
Title:
Hypersonic wind-tunnel free-flying experiments with onboard instrumentation
Authors:
Mudford, Neil R.; O'Byrne, Sean B.; Neely, Andrew J.; Buttsworth, David R.; Balage, Sudantha
Abstract:
Hypersonic wind-tunnel testing with "free-flight" models unconnected to a sting ensures that sting/wake flow interactions do not compromise aerodynamic coefficient measurements. The development of miniaturized electronics has allowed the demonstration of a variant of a new method for the acquisition of hypersonic model motion data using onboard accelerometers, gyroscopes, and a microcontroller. This method is demonstrated in a Mach 6 wind-tunnel flow, whose duration and pitot pressure are sufficient for the model to move a body length or more and turn through a significant angle. The results are compared with those obtained from video analysis of the model motion, the existing method favored for obtaining aerodynamic coefficients in similar hypersonic wind-tunnel facilities. The results from the two methods are in good agreement. The new method shows considerable promise for reliable measurement of aerodynamic coefficients, particularly because the data obtained are in more directly applicable forms of accelerations and rates of turn, rather than the model position and attitude obtained from the earlier visualization method. The ideal may be to have both methods operating together.
KAUST Department:
Physical Sciences and Engineering (PSE) Division; Mechanical Engineering Program
Publisher:
American Institute of Aeronautics and Astronautics (AIAA)
Journal:
Journal of Spacecraft and Rockets
Issue Date:
Jan-2015
DOI:
10.2514/1.A32887
Type:
Article
ISSN:
00224650
Appears in Collections:
Articles; Physical Sciences and Engineering (PSE) Division; Mechanical Engineering Program

Full metadata record

DC FieldValue Language
dc.contributor.authorMudford, Neil R.en
dc.contributor.authorO'Byrne, Sean B.en
dc.contributor.authorNeely, Andrew J.en
dc.contributor.authorButtsworth, David R.en
dc.contributor.authorBalage, Sudanthaen
dc.date.accessioned2015-08-03T12:22:27Zen
dc.date.available2015-08-03T12:22:27Zen
dc.date.issued2015-01en
dc.identifier.issn00224650en
dc.identifier.doi10.2514/1.A32887en
dc.identifier.urihttp://hdl.handle.net/10754/563998en
dc.description.abstractHypersonic wind-tunnel testing with "free-flight" models unconnected to a sting ensures that sting/wake flow interactions do not compromise aerodynamic coefficient measurements. The development of miniaturized electronics has allowed the demonstration of a variant of a new method for the acquisition of hypersonic model motion data using onboard accelerometers, gyroscopes, and a microcontroller. This method is demonstrated in a Mach 6 wind-tunnel flow, whose duration and pitot pressure are sufficient for the model to move a body length or more and turn through a significant angle. The results are compared with those obtained from video analysis of the model motion, the existing method favored for obtaining aerodynamic coefficients in similar hypersonic wind-tunnel facilities. The results from the two methods are in good agreement. The new method shows considerable promise for reliable measurement of aerodynamic coefficients, particularly because the data obtained are in more directly applicable forms of accelerations and rates of turn, rather than the model position and attitude obtained from the earlier visualization method. The ideal may be to have both methods operating together.en
dc.publisherAmerican Institute of Aeronautics and Astronautics (AIAA)en
dc.titleHypersonic wind-tunnel free-flying experiments with onboard instrumentationen
dc.typeArticleen
dc.contributor.departmentPhysical Sciences and Engineering (PSE) Divisionen
dc.contributor.departmentMechanical Engineering Programen
dc.identifier.journalJournal of Spacecraft and Rocketsen
dc.contributor.institutionSchool of Engineering and Information Technology, University of New South WalesCanberra, ACT, Australiaen
dc.contributor.institutionComputational Engineering and Science Research Centre, University of Southern QueenslandToowoomba, QLD, Australiaen
dc.contributor.institutionCentre for Hypersonics, University of QueenslandQLD, Australiaen
kaust.authorBalage, Sudanthaen
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