Usporedba različitih konfiguracija repa primjenom metode noseće linije

Cerinski, Damijan (2016) Usporedba različitih konfiguracija repa primjenom metode noseće linije. = Comparison of different tail configurations with application of lifting line method. Undergraduate thesis , Sveučilište u Zagrebu, Fakultet strojarstva i brodogradnje, UNSPECIFIED. Mentor: Vrdoljak, Milan.

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Abstract (Croatian)

Cilj ovog rada je postojeći model noseće linije modificirati za mogućnost analize različitih konfiguracija repa. Potrebno je odrediti gradijent normalne sile po napadnom kutu i gradijent bočne sile po kutu klizanja koji se koriste za određivanje uzdužne i poprečne statičke stabilnosti zrakoplova. Gradijent bočne sile po kutu klizanja određen je na način da se konfiguracija repa zarotirala za -90° oko uzdužne osi što predstavlja analogan problem određivanja gradijenta normalne sile po napadnom kutu. Rezultati su uspoređeni s eksperimentalnim i numeričkim rezultatima te računalnim programom XFLR5 čime je provjerena točnost metode.

Abstract

The aim of thesis is to modify lifting line method for ability to analyze different tail configuration. It is required to determine normal force gradient due to angle of attack and side force gradient due to sideslip angle whice are used to determine longitudinal and lateral static stability. Side force gradient due to sideslip angle is determine with rotated model around longitudinal axis for angle of -90° which present analogous problem of solving normal force gradient due to angle of attack. The results are compared with experimental and numerical results and with software XFLR5 whereby accuracy of method is veryfied.

Item Type:	Thesis (Undergraduate thesis)
Uncontrolled Keywords:	model noseće linije; gradijent normalne sile po napadnom kutu; gradijent bočne sile po kutu klizanja; konfiguracija V repa; konfiguracija obrnutog V repa; konvencionalna konfiguracija repa
Keywords (Croatian):	lifting line method; normal force gradient due to angle of attack; side force gradient due to sideslip angle; V tail configuration; reversed V tail configuration; conventional tail configuration
Subjects:	TECHNICAL SCIENCE > Aviation, rocket and space technology
Divisions:	1300 Department of Aeronautical Engineering > 1320 Chair of Aircraft Dynamics
Date Deposited:	26 Feb 2016 11:44
Last Modified:	26 Feb 2016 11:44
URI:	http://repozitorij.fsb.hr/id/eprint/5138

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