The effects of different wing configurations on missile aerodynamics
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| Název: | The effects of different wing configurations on missile aerodynamics |
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| Autoři: | Ahmet ŞUMNU, İbrahim GÜZELBEY |
| Přispěvatelé: | HKÜ, Mühendislik Fakültesi, Makine Mühendisliği Bölümü, Havacılık ve Uzay Bilimleri Fakültesi -- Havacılık ve Uzay Mühendisliği Bölümü, Şumnu, Ahmet |
| Zdroj: | Volume: 9, Issue: 5 1260-1271 Journal of Thermal Engineering |
| Informace o vydavateli: | Kare Publishing, 2023. |
| Rok vydání: | 2023 |
| Témata: | 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 |
| Popis: | 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. |
| Druh dokumentu: | Article |
| Popis souboru: | application/pdf |
| ISSN: | 2148-7847 |
| DOI: | 10.18186/thermal.1377200 |
| DOI: | 10.18186/thermal.00000 |
| Přístupová URL adresa: | 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 |
| Přístupové číslo: | edsair.doi.dedup.....86a06daef3cb9663526ee1c11ca901b0 |
| Databáze: | OpenAIRE |
Nájsť tento článok vo Web of Science | Abstrakt: | 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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| ISSN: | 21487847 |
| DOI: | 10.18186/thermal.1377200 |