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Author:Tuisku, Tuomas
Title:Ohjuksen tuulitunnelikokeiden mittausjärjestelyt
Test arrangements of a missile wind tunnel experiment
Publication type:Master's thesis
Publication year:2010
Pages:72 s. + liitt. 18      Language:   fin
Department/School:Sovelletun mekaniikan laitos
Main subject:Lentotekniikka   (Kul-34)
Supervisor:Soinne, Erkki
Instructor:Korhonen, Mikko
OEVS:
Electronic archive copy is available via Aalto Thesis Database.
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Location:P1 Ark TKK  2835   | Archive
Abstract (eng): The purpose of this master's thesis was to design a measurement arrangement to investigate high angle of attack aerodynamics of a generic missile in subsonic flow.
Force and moment measurements were carried out using an internal strain gauge balance.
The balance measured 6 components.

The missile model, used in the present investigation, is a 1:2,5-scale model of a typical modern short range IR-homing air-to-air or ground-to-air missile.
The missile has a canard-controlled configuration with tandem vanes in the front.
The geometry of the missile has been developed in the research group of aerodynamics.
The missile model and its mountings were designed within this work.

A series of wind tunnel tests were carried out in the subsonic wind tunnel of School of Technology and Science of Aalto University.
The measurements of the test section are 2,0*2,0 meters.
The test runs were made using three different nominal velocities, 30 m/s, 45 m/s and 60 m/s.
The corresponding Reynolds numbers, which are based on the diameter of the missile, are 1,38*105, 2,05*105 and 2,68*105.
The force and moment data were obtained at 10-degree intervals in the 0-60-degree angle of attack range at 0- degree bank angle.

The reduced data, which are presented in plot format, include the normal force coefficient, the pitching moment coefficient and the axial force coefficient.
For comparison, results of other researches are included.
The results match each other quite well, though differences can be found at high angles of attack.

With this test arrangement, wind tunnel experiments can proceed in order to acquire experimental data for verification and validation purposes.
Abstract (fin): Tämän työn tarkoituksena oli luoda mittausvalmius ohjuksen aerodynaamisten ominaisuuksien tutkimiseksi suurilla kohtauskulmilla alisoonisessa kokoonpuristumattomassa virtauksessa.
Voima- ja momenttimittaukseen käytettiin sisäistä 6- komponenttia mittaavaa venymäliuskavaakaa.

Tuulitunnelimalli on 1:2,5-pienoismalli tyypillisestä modernista lyhyen kantaman lämpöhakuisesta ohjuksesta.
Ohjus on canard-ohjattu ja varustettu tandem-etuevillä.
Ohjuksen geometria on kehitetty aerodynamiikan tutkimusryhmässä.
Tuulitunnelimalli kiinnityksineen suunniteltiin tämän työn puitteissa.

Koejärjestelyn verifioimiseksi suoritettiin sarja kokeellisia mittauksia Teknillisen korkeakoulun sovelletun mekaniikan laitoksen aerodynamiikan tutkimusryhmän alisoonisessa tuulitunnelissa, jonka mittatilan koko on 2,0 x 2,0 metriä.
Mittaukset suoritettiin kolmella nimellisnopeudella 30 m/s, 45 m/s ja 60 m/s, jolloin mallin halkaisijaan referoidut Reynoldsin luvut ovat vastaavasti 1,38*105, 2,05*105 ja 2,68*105.
Käytetty kohtauskulma alue oli 0 - 60 astetta, kallistuskulmaa ei varioitu nollasta.

Mittaustuloksista on esitetty normaalivoima-, aksiaalivoima- ja pituusmomenttikertoimet kuvaajien muodossa.
Vertailuksi on otettu mukaan kahden vastaavantyyppisen tutkimuksen tuloksia.
Tulokset ovat hyvin samansuuntaisia aina kohtauskulman arvoille 30 saakka, eroa syntyy etupäässä suurimmilla kohtauskulmilla.

Valmistuneella koejärjestelyllä voidaan jatkaa mittauksia kokeellisen mittaustiedon hankkimiseksi vertailu- ja muihin tarkoituksiin.
ED:2010-11-08
INSSI record number: 41277
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