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Author:Honkanen, Tomi
Title:Geneerisen ohjuksen CFD-simulointi
CFD simulation of a generic air-to-air missile
Publication type:Master's thesis
Publication year:2010
Pages:118 + [14]      Language:   fin
Department/School:Sovelletun mekaniikan laitos
Main subject:Lentotekniikka   (Kul-34)
Supervisor:Soinne, Erkki
Instructor:Kaarlonen, Kyösti
OEVS:
Electronic archive copy is available via Aalto Thesis Database.
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Location:P1 Ark Aalto  3155   | Archive
Abstract (eng): The objective of this master's thesis is to investigate the aerodynamic properties of a generic short-range air-to-air missile by means of CFD simulation.
Knowledge of the aerodynamic properties is needed in the Flight mechanics research group at Aalto University Department of Applied Mechanics to support missile flight simulation.

Usually air-to-air missiles fly at transonic and supersonic airspeeds but especially short-range missiles can manoeuvre in the subsonic speed range immediately after launch or during the final phase of their flight.
High angles of attack and flow separation are typical for these types of flight conditions.

The simulations were conducted with open source CFD software OpenFOAM.
The Aerodynamics research group did not have previous experience with the software.
Another objective of this master's thesis was to investigate the capabilities of the software in general.
Particularly of interest was the software's suitability for aerodynamics applications.
The software was first used to calculate simpler test cases like turbulent flat plate and the NACA 0012 airfoil.
The results of the calculations were compared with measured and calculated results found in literature.
The approach for more complicated missile simulations was chosen based on these comparisons.
The CFD simulations of the missile were performed at three Mach numbers, a few angles of attack and a couple of bank angles.
The total number of successful missile simulations was 15.
The results were compared with wind tunnel measurements performed simultaneously in the research group's subsonic wind tunnel.
Abstract (fin): Tässä diplomityössä tutkitaan laskennallisen virtausmekaniikan (CFD) keinoin geneerisen lyhyen kantaman ilmataisteluohjuksen aerodynaamisia ominaisuuksia alisoonisessa nopeusalueessa.
Tietoa ohjuksen aerodynaamisista ominaisuuksista tarvitaan Aalto- yliopiston sovelletun mekaniikan laitoksen lentomekaniikan tutkimusryhmässä ohjuksen lentomallinnuksen tueksi.

Ilmasta ilmaan -ohjukset lentävät yleensä transsoonisella tai ylisoonisella nopeusalueella, mutta erityisesti lähitaisteluohjukset saattavat liikehtiä alisoonisella nopeudella heti laukaisun jälkeen tai äkkinäisissä suunnanmuutoksissa lennon loppuvaiheessa.
Tällaisille lentotiloille on tyypillistä suuri kohtauskulma ja virtauksen irtoaminen laajalta alueelta.

Virtauslaskenta suoritettiin avoimeen lähdekoodiin perustuvalla OpenFOAM-ohjelmistolla.
Aerodynamiikan tutkimusryhmällä ei ollut aikaisempaa käyttökokemusta tästä ohjelmistosta, joten diplomityön tavoitteisiin kuului myös yleisemmin selvittää ohjelmiston ominaisuuksia ja sovellusmahdollisuuksia.
Ohjelmistolla tehtiin ensin yksinkertaisempia testilaskuja.
Testitapauksina käytettiin turbulenttista tasolevyä ja NACA 0012 -siipiprofiilia.
Tuloksia verrattiin kirjallisuudessa esiintyviin kokeellisiin tuloksiin ja muilla virtauslaskentaohjelmistoilla laskettuihin tuloksiin.
Näiden vertailujen perusteella valittiin lähestymistapa ohjuksen virtaussimulointiin.
Ohjuksen virtaussimulointeja tehtiin kolmella Machin luvulla ja muutamalla kohtaus- ja kallistuskulmalla.
Yhteensä ohjuslaskuja suoritettiin 15 kappaletta.
Simulointien tuloksia verrattiin tutkimusryhmässä samanaikaisesti tehtyjen tuulitunnelimittausten tuloksiin.
ED:2010-05-18
INSSI record number: 39655
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