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The effects of different wing configurations on missile aerodynamics

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Titel: The effects of different wing configurations on missile aerodynamics
Autoren: Ahmet ŞUMNU, İbrahim GÜZELBEY
Weitere Verfasser: HKÜ, Mühendislik Fakültesi, Makine Mühendisliği Bölümü, Havacılık ve Uzay Bilimleri Fakültesi -- Havacılık ve Uzay Mühendisliği Bölümü, Şumnu, Ahmet
Quelle: Volume: 9, Issue: 5 1260-1271
Journal of Thermal Engineering
Verlagsinformationen: Kare Publishing, 2023.
Publikationsjahr: 2023
Schlagwörter: Missile Aerodynamics, Turbulence Model, Missile WingConfiguration, CFD, Missile aerodynamics, Projectiles, Turbulence model, 02 engineering and technology, Missiles, Electrical Engineering, Electronics & Computer Science - Automation & Control Systems - Guidance Law, 01 natural sciences, Projectile, Thermodynamics and Statistical Physics, Shape optimization, 0203 mechanical engineering, Missile wing configuration, 0103 physical sciences, Termodinamik ve İstatistiksel Fizik, Missile Wing Configuration, Canard
Beschreibung: In the present study, missile aerodynamic analysis is performed using different wing config-urations at subsonic and transonic speeds. The wing is critical component in point of aero-dynamic efficiency for a missile that speed is especially closer to transonic level because of flow separation. Flow on the wings may adversely effect tailfins of missile at high speed since it may cause vortex generation and flow disturbances. There are few studies that investigate the missile wing using different configurations at critical speeds when examined the previ-ous studies. Therefore, in this study, three different wing configurations are investigated and aerodynamic performance is compared with each other at 0.7 and 0.9 Mach numbers and 5° angle of attack (AoA). In beginning of this study, missile model with only tailfins is selected from previous study that contains experimental data. Because the experimental data for the selected missile model are available at supersonic speeds, the aerodynamic analysis to verify the solutions is carried out at supersonic speeds. After wing is mounted to the selected missile, aerodynamic analysis is carried out using three different wing configurations that are Tapered Leading Edge, Tapered Trailing Edge, and Double Tapered wings. Lift to drag ratio (CL/CD) is calculated to compare wing configurations and it is concluded that Tapered Leading Edge wing configuration shows higher performance then other wing configurations. CL/CD values are 2.327, 2.306, 2.303 at 0.7 Mach number and 2.45, 2.429, 2.423 at 0.9 Mach number for Tapered Leading Edge, Tapered Trailing Edge, and Double Tapered, respectively. When the results are compared each other, CL/CD values at 0.9 Mach number is higher about % 5.28, %5.33 and %5.21 than the CL/CD values at 0.7 Mach number for missile with Tapered Leading Edge, Tapered Trailing Edge, and Double Tapered, respectively.
Publikationsart: Article
Dateibeschreibung: application/pdf
ISSN: 2148-7847
DOI: 10.18186/thermal.1377200
DOI: 10.18186/thermal.00000
Zugangs-URL: https://hdl.handle.net/20.500.11782/4041
https://doi.org/10.18186/thermal.00000
https://hdl.handle.net/20.500.12508/2983
https://dergipark.org.tr/tr/pub/thermal/issue/80447/1377200
Dokumentencode: edsair.doi.dedup.....86a06daef3cb9663526ee1c11ca901b0
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  Data: The effects of different wing configurations on missile aerodynamics
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  Data: <searchLink fieldCode="AR" term="%22Ahmet+ŞUMNU%22">Ahmet ŞUMNU</searchLink><br /><searchLink fieldCode="AR" term="%22İbrahim+GÜZELBEY%22">İbrahim GÜZELBEY</searchLink>
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  Data: HKÜ, Mühendislik Fakültesi, Makine Mühendisliği Bölümü<br />Havacılık ve Uzay Bilimleri Fakültesi -- Havacılık ve Uzay Mühendisliği Bölümü<br />Şumnu, Ahmet
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  Data: Volume: 9, Issue: 5 1260-1271<br />Journal of Thermal Engineering
– Name: Publisher
  Label: Publisher Information
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  Data: Kare Publishing, 2023.
– Name: DatePubCY
  Label: Publication Year
  Group: Date
  Data: 2023
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  Label: Subject Terms
  Group: Su
  Data: <searchLink fieldCode="DE" term="%22Missile+Aerodynamics%22">Missile Aerodynamics</searchLink><br /><searchLink fieldCode="DE" term="%22Turbulence+Model%22">Turbulence Model</searchLink><br /><searchLink fieldCode="DE" term="%22Missile+WingConfiguration%22">Missile WingConfiguration</searchLink><br /><searchLink fieldCode="DE" term="%22CFD%22">CFD</searchLink><br /><searchLink fieldCode="DE" term="%22Missile+aerodynamics%22">Missile aerodynamics</searchLink><br /><searchLink fieldCode="DE" term="%22Projectiles%22">Projectiles</searchLink><br /><searchLink fieldCode="DE" term="%22Turbulence+model%22">Turbulence model</searchLink><br /><searchLink fieldCode="DE" term="%2202+engineering+and+technology%22">02 engineering and technology</searchLink><br /><searchLink fieldCode="DE" term="%22Missiles%22">Missiles</searchLink><br /><searchLink fieldCode="DE" term="%22Electrical+Engineering%2C+Electronics+%26+Computer+Science+-+Automation+%26+Control+Systems+-+Guidance+Law%22">Electrical Engineering, Electronics & Computer Science - Automation & Control Systems - Guidance Law</searchLink><br /><searchLink fieldCode="DE" term="%2201+natural+sciences%22">01 natural sciences</searchLink><br /><searchLink fieldCode="DE" term="%22Projectile%22">Projectile</searchLink><br /><searchLink fieldCode="DE" term="%22Thermodynamics+and+Statistical+Physics%22">Thermodynamics and Statistical Physics</searchLink><br /><searchLink fieldCode="DE" term="%22Shape+optimization%22">Shape optimization</searchLink><br /><searchLink fieldCode="DE" term="%220203+mechanical+engineering%22">0203 mechanical engineering</searchLink><br /><searchLink fieldCode="DE" term="%22Missile+wing+configuration%22">Missile wing configuration</searchLink><br /><searchLink fieldCode="DE" term="%220103+physical+sciences%22">0103 physical sciences</searchLink><br /><searchLink fieldCode="DE" term="%22Termodinamik+ve+İstatistiksel+Fizik%22">Termodinamik ve İstatistiksel Fizik</searchLink><br /><searchLink fieldCode="DE" term="%22Missile+Wing+Configuration%22">Missile Wing Configuration</searchLink><br /><searchLink fieldCode="DE" term="%22Canard%22">Canard</searchLink>
– Name: Abstract
  Label: Description
  Group: Ab
  Data: In the present study, missile aerodynamic analysis is performed using different wing config-urations at subsonic and transonic speeds. The wing is critical component in point of aero-dynamic efficiency for a missile that speed is especially closer to transonic level because of flow separation. Flow on the wings may adversely effect tailfins of missile at high speed since it may cause vortex generation and flow disturbances. There are few studies that investigate the missile wing using different configurations at critical speeds when examined the previ-ous studies. Therefore, in this study, three different wing configurations are investigated and aerodynamic performance is compared with each other at 0.7 and 0.9 Mach numbers and 5° angle of attack (AoA). In beginning of this study, missile model with only tailfins is selected from previous study that contains experimental data. Because the experimental data for the selected missile model are available at supersonic speeds, the aerodynamic analysis to verify the solutions is carried out at supersonic speeds. After wing is mounted to the selected missile, aerodynamic analysis is carried out using three different wing configurations that are Tapered Leading Edge, Tapered Trailing Edge, and Double Tapered wings. Lift to drag ratio (CL/CD) is calculated to compare wing configurations and it is concluded that Tapered Leading Edge wing configuration shows higher performance then other wing configurations. CL/CD values are 2.327, 2.306, 2.303 at 0.7 Mach number and 2.45, 2.429, 2.423 at 0.9 Mach number for Tapered Leading Edge, Tapered Trailing Edge, and Double Tapered, respectively. When the results are compared each other, CL/CD values at 0.9 Mach number is higher about % 5.28, %5.33 and %5.21 than the CL/CD values at 0.7 Mach number for missile with Tapered Leading Edge, Tapered Trailing Edge, and Double Tapered, respectively.
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        Value: 10.18186/thermal.1377200
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      Pagination:
        PageCount: 12
        StartPage: 1260
    Subjects:
      – SubjectFull: Missile Aerodynamics
        Type: general
      – SubjectFull: Turbulence Model
        Type: general
      – SubjectFull: Missile WingConfiguration
        Type: general
      – SubjectFull: CFD
        Type: general
      – SubjectFull: Missile aerodynamics
        Type: general
      – SubjectFull: Projectiles
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        Type: general
      – SubjectFull: 02 engineering and technology
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      – SubjectFull: Missiles
        Type: general
      – SubjectFull: Electrical Engineering, Electronics & Computer Science - Automation & Control Systems - Guidance Law
        Type: general
      – SubjectFull: 01 natural sciences
        Type: general
      – SubjectFull: Projectile
        Type: general
      – SubjectFull: Thermodynamics and Statistical Physics
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      – SubjectFull: Shape optimization
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      – SubjectFull: 0203 mechanical engineering
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      – SubjectFull: Missile wing configuration
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      – SubjectFull: Missile Wing Configuration
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      – SubjectFull: Canard
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      – TitleFull: The effects of different wing configurations on missile aerodynamics
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