Analysis of flow structure in a helicopter cabin to improve the thermal comfort using cfd modeling

Date

2019-09-20

Author

Şahin, Doruk
Yavuz, Mehmet Metin

Metadata

Show full item record

Item Usage Stats

313
views

0
downloads

Proper distribution of conditioned air inside the cabins of passenger transportation type aircrafts is crucial in terms of passengers? comfort. In the present study, computational fluid dynamics (CFD) models are developed using ANSYS FLUENT to investigate the thermal comfort levels of the passengers in a newly designed passenger transportation helicopter. The results reveal that the performance of the existing personalized air distribution system of the helicopter is inadequate to provide a comfortable environment to the passengers. For the purpose of enhancing the thermal comfort levels of the passengers, an iterative procedure is followed to redesign the personalized air distribution system. The new design both provides the desired air velocities and effective distribution around the faces of passengers along with more uniform temperature distribution inside the cabin.'

URI

http://aiac.ae.metu.edu.tr
https://hdl.handle.net/11511/86892

Conference Name

10th Ankara International Aerospace Conference,18 - 20 Eylül 2019

Collections

Department of Mechanical Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Analysis of flow structure in a helicopter cabin to improve the thermal comfort using computational fluid dynamics modeling Şahin, Doruk; Yavuz, Mehmet Metin; Department of Mechanical Engineering (2018) Proper distribution of conditioned air inside the cabins of passenger transportation type aircrafts is crucial in terms of passengers’ comfort. Low air velocities may cause passengers to feel stuffy whereas high velocities may create disturbance. Moreover, satisfying uniform temperature distribution inside the cabin is also crucial for the passenger comfort. High temperature variation inside the cabin results in feeling of discomfort. In this thesis, computational fluid dynamics (CFD) models are developed u...
Investigation of fatigue behaviour of external stores under fixed wing aircraft platforms during random vibration Okur, Emre; Dağ, Serkan; Department of Mechanical Engineering (2015) In this study, fatigue behaviour of an external store during captive carriage at the underwing and wingtip of a fixed wing aircraft platform is investigated. The F-16C jet aircraft was determined as a fixed wing aircraft platform in this thesis which is commonly used by Turkish Army. As the external store, a data measurement store (DMS) was designed to measure loads during captive carrage. While the DMS was being attached to the F-16C jet aircraft, it flew in 5 different sorties. Acceleration and strain dat...
Design of an LPV Based Fractional Controller for the Vibration Suppression of a Smart Beam Onat, Cem; Şahin, Melin; Yaman, Yavuz; Eswar, Prasad; Saılu, Nemana (2011-12-01) One of the major problems encountered in the active vibration control of aircraft wings is the changing mass due to the in-flight fuel consumption. In this study, a Linear Parameter Varying (LPV) based fractional controller is designed for the suppression of the flexural vibrations of a smart beam. The designed controller is sensitive to the varying mass properties. The smart beam studied was a cantilever aluminium beam with eight surface bonded Lead-Zirconate-Titanate (PZT) patches. The smart beam was exci...
An algorithm for designing nonlinear springs, or nonlinear dampers, using a mechanical force generator and its application to an aircraft landing gear Yıldız, Fatih; Soylu, Reşit; Department of Mechanical Engineering (2021-12-03) The landing gear system is one of the most critical aircraft sub-systems that takes part in the landing, taxi and take-off phases of every aircraft. Its main function is the absorption of part of aircraft's kinetic energy during landing. There are different types of shock absorbers to perform this task. The performance of the shock absorbers has developed a lot after the invention of air-oil type shock absorbers. However, increasing the performance of these shock absorber elements is still a field of resear...
Determination of dynamically equivalent fe models of aircraft structures by using modal test data Karaağaçlı, Taylan; Özgüven, Hasan Nevzat; Yıldız, Erdinç N.; Department of Mechanical Engineering (2010) Reliable flutter analysis of aircraft structures is a major requirement to determine safe flight envelops. Dynamically equivalent finite element model of an aircraft structure correlating well with experimental modal is a major requirement for a reliable flutter analysis. Currently available model updating techniques require enormous time and engineering work to achieve appropriate finite element models of aircraft structures. The method developed within the scope of this thesis work aims to remove importan...

Citation Formats

D. Şahin and M. M. Yavuz, “Analysis of flow structure in a helicopter cabin to improve the thermal comfort using cfd modeling,” presented at the 10th Ankara International Aerospace Conference,18 - 20 Eylül 2019, Ankara, Türkiye, 2019, Accessed: 00, 2021. [Online]. Available: http://aiac.ae.metu.edu.tr.