Alemdaroğlu, Hüseyin Nafiz

Profile URL
https://hdl.handle.net/20.500.14411/7087
Name Variants
H.N.Alemdaroğlu Huseyin Nafiz, Alemdaroglu H.N.Alemdaroglu A.,Hüseyin Nafiz Alemdaroğlu, Hüseyin Nafiz Alemdaroğlu,H.N. H. N. Alemdaroglu Alemdaroglu,H.N. H., Alemdaroglu A.,Huseyin Nafiz A., Huseyin Nafiz Alemdaroglu, Huseyin Nafiz A., Hüseyin Nafiz H. N. Alemdaroğlu Hüseyin Nafiz, Alemdaroğlu H.,Alemdaroğlu Alemdaroğlu,N.
Job Title
Profesor Doktor
Email Address
nafiz.alemdaroglu@atilim.edu.tr
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Airframe and Powerplant Maintenance
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Scopus Author ID
57203431971
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Scholarly Output

3

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5/13

Supervised MSc Theses

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Supervised PhD Theses

1

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Scopus Citation Count

2

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0.00

Scopus Citations per Publication

0.67

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1

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JournalCount
2018 Applied Aerodynamics Conference -- 36th AIAA Applied Aerodynamics Conference, 2018 -- 25 June 2018 through 29 June 2018 -- [state] GA -- 2151091
2018 Fluid Dynamics Conference -- 48th AIAA Fluid Dynamics Conference, 2018 -- 25 June 2018 through 29 June 2018 -- Atlanta -- 2151391
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Now showing 1 - 3 of 3
  • Conference Object
    Citation - Scopus: 2
    Computational Fluid Dynamics Modelling of Store Separation for Transonic Generic Store
    (American Institute of Aeronautics and Astronautics Inc, AIAA, 2018-06-24) Demir,G.; Alemdaroğlu,N.
    In this study, two different well-known wind tunnel techniques; “Captive Trajectory Method “and “Grid Surveying Method “are simulated using Computational Fluid Dynamics (CFD) method. Time dependent behavior of a generic store during the release process from a delta wing under high transonic flow regime is determined. First of all, in captive trajectory simulation, simultaneous trajectory and attitude computations are accomplished by utilizing a reliable commercial flow solver called ANSYS Fluent. Secondly, aerodynamic grid database generation required for grid surveying approach is performed and the trajectory of the store is determined by using a standalone store separation module built in MATLAB Simulink. The numerical outputs are compared with available wind tunnel results conducted in Arnold Engineering Development Center. © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
  • Conference Object
    Design and Performance Analysis of Double-Flux Supersonic Air Ejector
    (American Institute of Aeronautics and Astronautics Inc, AIAA, 2018-06-24) Bozkir,B.; Alemdaroğlu,H.N.
    The main purpose of this study is to design a double-flux supersonic ejector and to evaluate its performance associated with its entrainment ratio by employing Computational Fluid Dynamics methods as well as one-dimensional approach. Since the performance of the ejector systems are strongly dependent on the design, this study concentrates on maximizing the entrainment ratio by varying the corresponding angles and the lengths of the critical segments such as mixing angle, divergence angle, mixing throat length etc., while keeping the operational parameters unaltered. Numerically computed results and the one-dimensional calculations have been compared. It is understood that the proper design is mandatory for achieving efficient entrainment ratios and has prominent effect on the operation of the system. It is found that almost 20% of enhancement on entrainment performance can be obtained solely by modifying the lengths and angles of the ejector’s critical segments without changing the operating conditions. It is also deduced that during these modifications, the complex flow structure through the system should not be disregarded for a thoroughly maximization of the performance and an efficient operation of the ejector. © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
  • Doctoral Thesis
    Melez (çok Modlu) Bir Uçan Robot Sınıfının Kapalı Çevrim Dinamiği
    (2020) Battı, Mohamed Ismaıl; Arıkan, Kutluk Bilge; Alemdaroğlu, Hüseyin Nafiz
    Bu çalışmada, basit ve ileri seviyeden oluşan melez bir uçan robot sınıfı önerilmiştir. Her iki sistem için iki boyutlu uzayda doğrusal ve doğrusal olmayan modeller çıkarılmıştır. Doğrusal kuadratik regülatör temelli denetim sistemleri, askı durumu ve navigasyon senaryolarına yönelik olarak tasarlanmıştır. Benzetimlerde bozucu dış kuvvetler dikey kalkış, ileri uçuş ve iniş sırasında etki etmiştir. Senaryolar esnasında basit ve ileri seviye sistemlerin dinamik davranışlarının karşılaştırılmasının yanında her bir sistem için doğrusal ve doğrusal olmayan sistem cevapları da değerlendirilmiştir. Admitans tipi denetimcinin, zorlayıcı dış kuvvetlerin etki ettiği hallerde basit sisteminin kararlılığını sağladığı benzetimler ile sunulmuştur. Her iki sistem de kara-hava melez sistem olarak ve hava manipülatörü olarak kullanıma uygun olduğu sunulmuştur.