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Title:Poraba goriva motornega zmaja v odvisnosti od hitrosti letenja in nastavitve kota propelerja
Authors:Gajser, Tomaž (Author)
Kegl, Breda (Mentor) More about this mentor... New window
Pehan, Stanislav (Co-mentor)
Files:.pdf UN_Gajser_Tomaz_2016.pdf (4,83 MB)
MD5: F78BB7D1D4BABFBEDDBF1931ECD8F3E4
 
Language:Slovenian
Work type:Undergraduate thesis (m5)
Typology:2.11 - Undergraduate Thesis
Organization:FS - Faculty of Mechanical Engineering
Abstract:Diplomsko delo zajema teoretične osnove, pripravo in letenje z motornim zmajem v različnih razmerah in merjenje porabe goriva. Spreminjali smo hitrost letenja in vpadni kot propelerja na vnaprej določeni poti (ruti) letenja. Po vsakem letu smo izmerili natančno in po vnaprej definiranem vrstnem redu porabljeno količino goriva. Cilj diplomskega dela je določitev hitrosti letenja motornega zmaja in nastavitev kota propelerja, ob katerih je mogoče preleteti največjo razdaljo s točno določeno količino goriva. Najmanjša poraba pri našem motornem zmaju je bila pri hitrosti letenja 70 km/h in pri 8° vpadnega kota propelerja. S takšnimi nastavitvami in hitrostjo letenja bi za preletenih 100 km porabili 9090 g goriva, če upoštevamo tudi vzlet in pristanek. Iz naših meritev in ugotovitev lahko povzamemo tudi splošne ugotovitve, ki veljajo za druge motorne zmaje in podobna zračna plovila. Najmanjša poraba pri motornem zmaju je pri hitrosti letenja v točki največjega drsnega števila in ob najmanjšem še mogočem vpadnem kotu propelerja.
Keywords:motorni zmaj, profil krila, krilo, propeler, kot propelerja, poraba goriva, vpadni kot, hitrost letenja, Pipistrel, Rotax, Hazard
Year of publishing:2016
Publisher:[T. Gajser]
Source:Maribor
UDC:629.734.34(043.2)
COBISS_ID:20307734 New window
NUK URN:URN:SI:UM:DK:VRNOZ89C
Views:879
Downloads:52
Metadata:XML RDF-CHPDL DC-XML DC-RDF
Categories:KTFMB - FS
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Secondary language

Language:English
Title:The fuel consumption of powered hang glider as a function of airspeed and propeller angle settings
Abstract:Present diploma paper represents the theoretic framework, preparation and flying with a powered hang glider under different conditions, as well as measurements of fuel consumption. During different tests on the predetermined route the airspeed of the powered hang glider and the propeller pitch have been changed. After each flight, the fuel consumption has been precisely measured. The process of measurement was exactly predefined. The goal of the diploma paper was to determine the flight velocity of the powered hang glider and the adjustment of the propeller pitch, whereby the longest distance could be flown with the exact quantity of fuel. The minimum fuel consumption of our powered hang glider has been reached at the airspeed of 70 km/h with the propeller pitch of eight degrees. With those adjustments and speed, the powered hang glider will consume 9,090 g of fuel per 100 km, including the fuel consumption at take-off and landing. According to our measurements and findings, we could determine that our conclusions are applicable for other powered hang gliders and similar aircrafts. The minimum fuel consumption of the powered hang glider at flying speed is achieved when the glide ratio is at its highest point and the propeller pitch is at its minimum possible angle.
Keywords:powered hang glider, wing profile, wing, propeller, propeller pitch, fuel consumption, attack angle, flying speed, Pipistrel, Rotax, Hazard


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