Aerodynamic interference in full helicopter configurations: Validation using the helinovi database

Visingardi, A; Dummel, A; Falchero, D; Pidd, M; Voutsinas, SG; Yin, J

dc.contributor.author	Visingardi, A	en
dc.contributor.author	Dummel, A	en
dc.contributor.author	Falchero, D	en
dc.contributor.author	Pidd, M	en
dc.contributor.author	Voutsinas, SG	en
dc.contributor.author	Yin, J	en
dc.date.accessioned	2014-03-01T02:51:02Z
dc.date.available	2014-03-01T02:51:02Z
dc.date.issued	2007	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/35310
dc.relation.uri	http://www.scopus.com/inward/record.url?eid=2-s2.0-34547593392&partnerID=40&md5=499b4f483d71e5f6b82c6a3434f78830	en
dc.subject	Aerodynamic interference	en
dc.subject	Helicopter	en
dc.subject	HeliNOVI	en
dc.subject	Numerical simulation	en
dc.subject	Tail rotor noise reduction	en
dc.subject.other	Aerodynamics	en
dc.subject.other	Computational fluid dynamics	en
dc.subject.other	Database systems	en
dc.subject.other	Vortex flow	en
dc.subject.other	Aerodynamic interference	en
dc.subject.other	Tail rotor noise reduction	en
dc.subject.other	Helicopters	en
dc.title	Aerodynamic interference in full helicopter configurations: Validation using the helinovi database	en
heal.type	conferenceItem	en
heal.publicationDate	2007	en
heal.abstract	The present paper summarizes the results obtained during the validation phase of the aerodynamic computational tools performed in the framework of the European research project HeliNOVI and relative to the interactional phenomena arising on a full helicopter configuration. The activity was carried out by exploiting the experimental database produced during the wind tunnel test campaign of the project for a 40% Mach and dynamically scaled BO105 helicopter model. Seven test cases were performed. A climb, a descent and a level flight were chosen as baseline test cases aiming at highlighting the phenomenological differences among three main helicopter flight conditions. The remaining four were dedicated to the analysis of possible tail rotor (TR) modifications in order to alleviate those interactional aspects responsible for high TR noise emissions. The experimental results indicate a low influence of the main rotor (MR) as source noise in 12° climb and 60m/s level flight whereas a predominance during the descent flight because of MR blade vortex interactions. Conversely, the TR noise represents the main source of noise especially in climb flight whereas is irrelevant during the descent flight. The modification of the TR operational characteristics is effective in reducing the interactional aspects and thus the noise emission. The numericalexperimental comparisons highlight the extreme complexity of the aerodynamic phenomena arising on a helicopter during flight. The numerical computations sometimes provide different predictions. It is a common opinion that they are motivated by the summation of the differences in the methodologies as well as trim procedures applied rather than by a specific reason only.	en
heal.journalName	National Aerospace Laboratory NLR - 32nd European Rotorcraft Forum, ERF 2006	en
dc.identifier.volume	1	en
dc.identifier.spage	530	en
dc.identifier.epage	549	en