A METHODOLOGY FOR THE ANALYSES OF UNSTEADY FLOWFIELDS AROUND FORWARD FLYING HELICOPTER ROTORS
This study presents the outcomes of a series of computational fluid dynamics analyses conducted to obtain unsteady solutions of the flowfields around single rotor helicopter configurations. We use a methodology to obtain the time dependent solutions of the 3D, compressible Navier Stokes equations ad...
| Main Authors: | , |
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| Format: | Article |
| Language: | English |
| Published: |
Turkish Air Force Academy
2018-07-01
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| Series: | Havacılık ve Uzay Teknolojileri Dergisi |
| Subjects: | |
| Online Access: | http://www.jast.hho.edu.tr/JAST/index.php/JAST/article/view/327/276 |
| _version_ | 1797921525890809856 |
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| author | Murat Gecgel Yavuz Nacaklı |
| author_facet | Murat Gecgel Yavuz Nacaklı |
| author_sort | Murat Gecgel |
| collection | DOAJ |
| description | This study presents the outcomes of a series of computational fluid dynamics analyses conducted to obtain unsteady solutions of the flowfields around single rotor helicopter configurations. We use a methodology to obtain the time dependent solutions of the 3D, compressible Navier Stokes equations adapted for a rotating frame of reference. In order to carry out the simulations, the developed mathematical model is solved on hybrid meshes to optimally benefit the advantages of both the structured and the unstructured grids. For the entire flowfield calculations, one-equation Spalart-Allmaras turbulence model is employed. To decrease the computational time and memory requirements, parallel processing with distributed memory is utilized. We validate the developed model and the simulation methodology by comparing the results with the published experimental data. In the following phase of the study, the unsteady calculations of the flowfields around single, two bladed helicopter rotor configurations are conducted for hover and forward flight cases. As the forward flight speed increases, development of the dissymmetry of lift on advancing and retreating blades has been observed for six advance ratios. These time–accurate computations help to analyze the adverse effect of increasing forward flight speed in order especially to determine the never-exceed speed for single rotor helicopter configurations. |
| first_indexed | 2024-04-10T14:17:11Z |
| format | Article |
| id | doaj.art-15cf4ec4a7d74b2d9ff21aaf05569660 |
| institution | Directory Open Access Journal |
| issn | 1304-0448 1304-0448 |
| language | English |
| last_indexed | 2024-04-10T14:17:11Z |
| publishDate | 2018-07-01 |
| publisher | Turkish Air Force Academy |
| record_format | Article |
| series | Havacılık ve Uzay Teknolojileri Dergisi |
| spelling | doaj.art-15cf4ec4a7d74b2d9ff21aaf055696602023-02-15T16:09:28ZengTurkish Air Force AcademyHavacılık ve Uzay Teknolojileri Dergisi1304-04481304-04482018-07-011127182A METHODOLOGY FOR THE ANALYSES OF UNSTEADY FLOWFIELDS AROUND FORWARD FLYING HELICOPTER ROTORSMurat Gecgel0Yavuz Nacaklı1Turkish Air Force Academy Turkish Air Force Academy This study presents the outcomes of a series of computational fluid dynamics analyses conducted to obtain unsteady solutions of the flowfields around single rotor helicopter configurations. We use a methodology to obtain the time dependent solutions of the 3D, compressible Navier Stokes equations adapted for a rotating frame of reference. In order to carry out the simulations, the developed mathematical model is solved on hybrid meshes to optimally benefit the advantages of both the structured and the unstructured grids. For the entire flowfield calculations, one-equation Spalart-Allmaras turbulence model is employed. To decrease the computational time and memory requirements, parallel processing with distributed memory is utilized. We validate the developed model and the simulation methodology by comparing the results with the published experimental data. In the following phase of the study, the unsteady calculations of the flowfields around single, two bladed helicopter rotor configurations are conducted for hover and forward flight cases. As the forward flight speed increases, development of the dissymmetry of lift on advancing and retreating blades has been observed for six advance ratios. These time–accurate computations help to analyze the adverse effect of increasing forward flight speed in order especially to determine the never-exceed speed for single rotor helicopter configurations.http://www.jast.hho.edu.tr/JAST/index.php/JAST/article/view/327/276HelicopterForward FlightTurbulence modelComputational Fluid DynamicsHybrid mesh |
| spellingShingle | Murat Gecgel Yavuz Nacaklı A METHODOLOGY FOR THE ANALYSES OF UNSTEADY FLOWFIELDS AROUND FORWARD FLYING HELICOPTER ROTORS Havacılık ve Uzay Teknolojileri Dergisi Helicopter Forward Flight Turbulence model Computational Fluid Dynamics Hybrid mesh |
| title | A METHODOLOGY FOR THE ANALYSES OF UNSTEADY FLOWFIELDS AROUND FORWARD FLYING HELICOPTER ROTORS |
| title_full | A METHODOLOGY FOR THE ANALYSES OF UNSTEADY FLOWFIELDS AROUND FORWARD FLYING HELICOPTER ROTORS |
| title_fullStr | A METHODOLOGY FOR THE ANALYSES OF UNSTEADY FLOWFIELDS AROUND FORWARD FLYING HELICOPTER ROTORS |
| title_full_unstemmed | A METHODOLOGY FOR THE ANALYSES OF UNSTEADY FLOWFIELDS AROUND FORWARD FLYING HELICOPTER ROTORS |
| title_short | A METHODOLOGY FOR THE ANALYSES OF UNSTEADY FLOWFIELDS AROUND FORWARD FLYING HELICOPTER ROTORS |
| title_sort | methodology for the analyses of unsteady flowfields around forward flying helicopter rotors |
| topic | Helicopter Forward Flight Turbulence model Computational Fluid Dynamics Hybrid mesh |
| url | http://www.jast.hho.edu.tr/JAST/index.php/JAST/article/view/327/276 |
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