000			03533nam a22003855i 4500
001			299552
003			MX-SnUAN
005			20160429155553.0
007			cr nn 008mamaa
008			150903s2009 gw | o |||| 0|eng d
020			_a9783642017605 _99783642017605
024	7		_a10.1007/9783642017605 _2doi
035			_avtls000353164
039		9	_a201509030522 _bVLOAD _c201405060316 _dVLOAD _y201402180938 _zstaff
040			_aMX-SnUAN _bspa _cMX-SnUAN _erda
050		4	_aTA357-359
100	1		_aGinevsky, A.S. _eautor _9336540
245	1	0	_aVortex wakes of Aircrafts / _cby A.S. Ginevsky, A. I. Zhelannikov.
264		1	_aBerlin, Heidelberg : _bSpringer Berlin Heidelberg, _c2009.
300			_brecurso en línea.
336			_atexto _btxt _2rdacontent
337			_acomputadora _bc _2rdamedia
338			_arecurso en línea _bcr _2rdacarrier
347			_aarchivo de texto _bPDF _2rda
490	0		_aFoundations of Engineering Mechanics, _x1612-1384
500			_aSpringer eBooks
505	0		_aGeneral -- Discrete Vortex Method -- The Near Vortex Wake Behind a Single Aircraft -- Far Vortex Wake Behind a Turbojet Aircraft -- Vortex Wakes Behind Propeller-Driven Aircraft -- Wind Flow Over Rough Terrain -- Simulation of the Far Vortex Wake of an Aircraft at Takeoff and Landing -- Aerodynamic Loads on Aircraft Encountering Vortex Wakes of Other Aircraft.
520			_aThe book presents methods of mathematical modeling of vortex wakes of aircraft in flights at high altitudes and close to the ground at take-off-landing regimes. The modeling is based on an extensive application of the method of discrete vortices in aircraft flights at high altitudes and on a conjugation of this method with the integral method of predicting the turbulent boundary layer which is produced at the secondary wall transversal flow induced by the aircraft vertex system at take-of-landing regimes. In this latter case an interaction between the vortex wake of aircraft and the secondary vortices generated at boundary layer separations is taken into account. The authors consider separately methods of modeling the near and far vortex wakes of aircrafts with turbojets and air propellers and they present the results of predicting vortex wakes of a series of domestic and foreign aircrafts. The effect of number of factors is taken into account in these cases: turbulence and atmosphere stratification, presence of side wind at take- off-landing regimes. The computer time consumption while modeling the vortex wakes according to the proposed method is 3 - 4 orders less than in the case of using the well-known numerical methods. The non-linear non-stationary mathematical model of light aircraft movement when they enter the vortex wake of a heavy aircraft with a description of possible catastrophic consequences for the light aircraft is considered separately. A comparison between the prediction data and the experimental results is given. The book is intended for researchers and engineers, as well as for lecturers, post-graduate and undergraduate students.
590			_aPara consulta fuera de la UANL se requiere clave de acceso remoto.
700	1		_aZhelannikov, A. I. _eautor _9336541
710	2		_aSpringerLink (Servicio en línea) _9299170
776	0	8	_iEdición impresa: _z9783642017599
856	4	0	_uhttp://remoto.dgb.uanl.mx/login?url=http://dx.doi.org/10.1007/978-3-642-01760-5 _zConectar a Springer E-Books (Para consulta externa se requiere previa autentificación en Biblioteca Digital UANL)
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999			_c299552 _d299552