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АЭРОДИНАМИЧЕСКИЕ ХАРАКТЕРИСТИКИ НАДУВНОГО ДЕФОРМИРУЕМОГО КРЫЛА

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  1. Tez No: 403081
  2. Yazar: GÜRKAN ORTAMEVZİ
  3. Danışmanlar: DR. DMITRY ZINCHENKO
  4. Tez Türü: Doktora
  5. Konular: Havacılık Mühendisliği, Aeronautical Engineering
  6. Anahtar Kelimeler: aircraft wing with a soft skin, aerodynamics characteristics, deformable wing, method computational aerodynamics, aircraft, inflatable wing, soft wing, hybrid wing, combine wing
  7. Yıl: 2017
  8. Dil: Rusça
  9. Üniversite: National Aviation University
  10. Enstitü: Yurtdışı Enstitü
  11. Ana Bilim Dalı: Belirtilmemiş.
  12. Bilim Dalı: Belirtilmemiş.
  13. Sayfa Sayısı: 155

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Özet (Çeviri)

The work is devoted to calculational and experimental assessment of the aerodynamic characteristics of a deformable inflatable wing. It is shown that in thesis analysis is performed design aircraft carrier with a soft surface, considered especially their aerodynamics, defined scientific novelty research, the goals and objectives of the work. Based on the analysis of deformable wing aerodynamics, performed the assessment method applicability computational aerodynamics to the task. Has been completed wing aerodynamic analysis, which has a soft and rigid part with different width. To determining the optimal width of the soft parts of the wing, as well as evaluation of its effect, the experiment has been carried out in a wind tunnel. The analysis of the comparison of methods of computational aerodynamics (finite element method, and panel-vortex method) for the rigid wing and wing with soft skin that includes a rigid front part of the chord (30%) and soft skin back (70%). In thesis presents the results of flight and ground test bench flying model aircraft with the original wing and wing with inflatable soft tail. The method of identifying the characteristics of aerodynamics flying model on the basis of objective control the autopilot. The comparison of the results with the baseline characteristics of the aircraft. During the ground test bench peculiarities flow wing inflatable tail, we get the actual deformation of the bearing surface of the type proposed, identify the areas of flow separation at the beginning of the proposed bearing surface. During the flight test assesses the characteristics of stability and controllability of a flying wing models with the type proposed. Studied the characteristics of the experimental and numerical models, as well as a comparative analysis of performance of aircraft with different types of wing skin with equal specific wing loading G / S.

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