Generalized reference enthalpy formulations and simulation of viscous effects in hypersonic flow

Simeonides, G

dc.contributor.author	Simeonides, G	en
dc.date.accessioned	2014-03-01T01:13:46Z
dc.date.available	2014-03-01T01:13:46Z
dc.date.issued	1998	en
dc.identifier.issn	0938-1287	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/12713
dc.relation.uri	http://www.scopus.com/inward/record.url?eid=2-s2.0-19444385834&partnerID=40&md5=924576bdc5ff5a1921be89272ee79576	en
dc.subject	Heat transfer	en
dc.subject	Hypersonic flow	en
dc.subject	Hypersonic similitude	en
dc.subject	Radiation-equilibrium	en
dc.subject	Reference enthalpy	en
dc.subject	Skin friction	en
dc.subject	Viscous (temperature) effects	en
dc.subject.classification	Mechanics	en
dc.title	Generalized reference enthalpy formulations and simulation of viscous effects in hypersonic flow	en
heal.type	journalArticle	en
heal.language	English	en
heal.publicationDate	1998	en
heal.abstract	A generalized reference enthalpy formulation for the skin friction, heat transfer and radiation-equilibrium temperature distributions over aerodynamic surfaces in attached hypersonic / hyperenthalpic flow is proposed. The formulation, which has been extensively employed in various forms by numerous investigators in the perfect gas regime, has also been recently demonstrated to provide adequate estimates of the heat transfer distribution in thermochemically active high enthalpy flow conditions when coupled to thermochemically active Euler solutions. It is now used to reveal the relevant similitude parameters for viscous effects in hypersonic flow, and the importance of the temperature distribution across the boundary layer and of the temperature-viscosity relation. It is shown that, although reproduction of the flight total flow enthalpy as well as surface temperature is the obvious solution for full viscous simulation in (perfect gas) hypersonic flow, the hot surface testing requirement and, in a number of practical applications, also the hot flow requirement may be relaxed with reasonably small error that can be of the same order as the measurement accuracy in present-day hypersonic testing. This similitude error, however, may increase significantly in cases exhibiting strong viscous/inviscid interaction or when the laminar-turbulent transition process becomes important. In this respect, alternative full simulation solutions, which are less demanding in terms of reproduction of the high levels of flight freestream and surface temperature or even Reynolds number, are discussed. © Springer Verlag 1998.	en
heal.publisher	SPRINGER VERLAG	en
heal.journalName	Shock Waves	en
dc.identifier.isi	ISI:000074460100004	en
dc.identifier.volume	8	en
dc.identifier.issue	3	en
dc.identifier.spage	161	en
dc.identifier.epage	172	en