Shock-tunnel skin-friction measurement in a supersonic combustor

Stalker, RJ and Paull, A (1999) Shock-tunnel skin-friction measurement in a supersonic combustor. Journal of Propulsion and Power, 15 5: 699-705. doi:10.2514/2.5481

Author Stalker, RJ
Paull, A
Title Shock-tunnel skin-friction measurement in a supersonic combustor
Journal name Journal of Propulsion and Power   Check publisher's open access policy
ISSN 0748-4658
Publication date 1999-01-01
Sub-type Article (original research)
DOI 10.2514/2.5481
Volume 15
Issue 5
Start page 699
End page 705
Total pages 7
Place of publication Reston, Va
Publisher American Institute of Aeronautics and Astronautics
Language eng
Subject C1
290299 Aerospace Engineering not elsewhere classified
690302 Space transport
Abstract Shock-tunnel measurements are reported of skin friction with supersonic hydrogen-air combustion in a constant area duct. A floating-element skin-friction gauge was used, in which the shear force was applied directly to a piezoceramic measuring element. The experiments were conducted at stagnation enthalpies of 5.7 and 6.8 MJ kg(-1), a precombustion Mach number of similar to 4.5, and with a maximum duct Reynolds number of 1.3 x 10(7). The measurements showed that, although supersonic combustion caused the skin friction to fluctuate with time, it did not affect the mean value of the skin friction coefficient, and this mean value could be predicted using existing turbulent: boundary-layer theory. Measurements of heat transfer also established that Reynolds analogy could be used in both the fuel-off and fuel-on flows.
Keyword Engineering, Aerospace
Q-Index Code C1

Document type: Journal Article
Sub-type: Article (original research)
Collection: School of Civil Engineering Publications
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Created: Tue, 10 Jun 2008, 23:42:15 EST