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## Preliminary aerodynamic design and wind tunnel tests of unmanned aircraft

#### Abstract

xxxUAV- Unmanned Aerial Vehicle (Polish mark: BSL) is engine powered air vehicle, remote controlled or with autonomous mission profile (may be submitted combination of these control ways), which can be used many times. UAV is able to carry mission payloads and special equipment to be configured for range of applications. There are many different types of UAV with wide spectrum of technical and flight abilities, sizes and weights. Construction and equipment of this vehicles depends on range of mission, take off weight, take off and landing techniques, and especially mission profile. UAVs are very useful because of low time and cost of exploitation and lower production cost than in case of airplanes. By the other hand, in UAV case, there is no limit of human pilot endurance (who can bare maximum 10g), so manned aircrafts could be easier target for anti-aircraft artillery. Experts are anticipating dynamic development of UAVs in military and multipurpose version. This publication contains shortened description of aerodynamic shape design of unmanned air vehicle, 88.5lb takeoff weight, with piston engine. There are described developed constructions in this class of UAV, their configurations and basic data. For easy components arrange and weight analyses, there was performed 3D model of whole aircraft in UNIGRAPHICS NX3. There was checked possibility of gravity center proper position in different payload and fuel configurations. In analytic calculations there where obtained moments of inertia of main components of airframe and equipment in different payload and fuel configurations. Aerodynamic characteristics of aerofoil CL(α), CD(α), CmyS.A.(α) (Polish marks: Cz(α), Cx(α), CmS.A.(α)), were obtained after numerical calculations in XFOIL. Aerofoil which was chosen for this aircraft was previously optimized for maximum L/D. Obtained characteristics for aerofoil were subject to analytical calculations to get characteristics for wing with finished span. Next task, in this publication, were calculations of forces and moments from each part of airframe, landing gears, tails etc. Position of under fuselage spherical camera, was optimized to get the lowest interference drag. In this way were obtained analytical aerodynamic characteristics of whole aircraft, its maximum L/D and energetic function. Last step, of analytical calculations, was relating to longitudinal moment of aircraft, including moments from wing, fuselage, horizontal tail and propeller. For wind tunnel applications, author has made model of UAV which has 27.3in wing span. Wind tunnel tests were done in conditions of dynamic pressure: q=100mmH2O, which is corresponding to Reynolds number: Re=200 000. The tests task were aerodynamic characteristics: CL(α), CD(α), CmyS.A.(α) for a Î (- 25 ;25 ) without tailerone deflections, and same characteristics for tailerone deflections: δH=(–30°;+30°) with 10° step. Next task was to obtain characteristics of side force and moment during side slip in range of slip angle β=(-15°;+15°) for four angles of attack α=(0°,10°,15°,20°). During analyzes of CL 2(CD) characteristic, for flow visualization there were chosen few angles of attack: α=(-2°÷-4°,0°,7°÷8°,10°÷12°,17°). This angles are 5 corresponding to: places where linear characteristic is collapsing, maximum CL value, so there were expected some changes of flow character. Flow visualization was performed in two ways: oil film method and flow direction indicator. Last task was to get aerodynamic characteristics of model without tail unit for range of angle of attack:a Î (- 25 ;25 ). Obtained characteristics from wind tunnel tests, were compared to analytical on common figures.
Diploma type
Engineer's / Bachelor of Science
Diploma type
Engineer's thesis
Author
Adam Markiewicz (FPAE) Adam Markiewicz,, Faculty of Power and Aeronautical Engineering (FPAE)
Title in Polish
Wstępny projekt aerodynamiczny i badania tunelowe samolotu bezzałogowego
Supervisor
Krzysztof Kubryński (FPAE/IAAM) Krzysztof Kubryński,, The Institute of Aeronautics and Applied Mechanics (FPAE/IAAM)Faculty of Power and Aeronautical Engineering (FPAE)
Certifying unit
Faculty of Power and Aeronautical Engineering (FPAE)
Affiliation unit
The Institute of Aeronautics and Applied Mechanics (FPAE/IAAM)
Study subject / specialization
, Mechanika i Budowa Maszyn
Language
(pl) Polish
Status
Finished
Defense Date
30-05-2007
Issue date (year)
2007
Pages
95
Internal identifier
MEL; PD-353
Reviewers
Krzysztof Kubryński (FPAE/IAAM) Krzysztof Kubryński,, The Institute of Aeronautics and Applied Mechanics (FPAE/IAAM)Faculty of Power and Aeronautical Engineering (FPAE) Jerzy Maryniak Jerzy Maryniak,, Undefined Affiliation
Keywords in Polish
PROJEKTOWANIE SAMOLOTÓW, SAMOLOTY BEZZAŁOGOWE, BADANIA AERODYNAMICZNE, BADANIA TUNELOWE, PROJEKTOWANIE AERODYNAMICZNE, LOTNICTWO I KOSMONAUTYKA
Keywords in English
xxx
Abstract in Polish
urn:pw-repo:WUTd5d8cbdf513d47abbbe6e02172f83aff