Optimization of S-Shaped Air Intake by Computational Fluid Dynamics

Hamid Parhrizkar; Kiumars Khani Aminjan; Mohammad Mahdi Doustdar; Ahad Heydari

doi:doi:10.11648/j.ijfmts.20190502.11

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Optimization of S-Shaped Air Intake by Computational Fluid Dynamics

Hamid Parhrizkar, Kiumars Khani Aminjan, Mohammad Mahdi Doustdar, Ahad Heydari

Published in International Journal of Fluid Mechanics & Thermal Sciences (Volume 5, Issue 2)

Received: 21 March 2019 Accepted: 10 May 2019 Published: 4 June 2019

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Abstract

Due to the presence of air intakes outside the body of some missiles with research objectives as well as some unmanned aerial, the use of the air intake duct in S-shaped is necessary and therefore the air flow quality must be determined, with the most important parameters being the total drop and distortion is from the beginning of the air intake until the delivery phase to the engine. In this research, it has been determined that the optimum air intake geometry is determined according to the dimensions of a unmanned aerial. Therefore, we first tried to optimize the geometry of S-shaped air intake and then optimize this geometry based on the reduction of total pressure drop. The computational grid with ICEM software and mesh analysis by computational fluid dynamics (Fluent software) has been done. Given that the intake of unmanned aerial was considered in this study, Mach flight is considered 0.3. Since the output section is actually the same section of the motor, whose cross section is constant, it has been considered in optimizing the inlet section and the wall. By optimizing geometry, the total pressure drop dropped to about half. Given the fact that the optimization repetition resulted in undesirable changes in geometry, optimization of geometry was not repeated. Additionally, by comparing the optimized geometry with the initial geometry, It is known that the slow rotation of the flow (the lower rotation angle) reduces the total pressure drop and reduces the amount of distortion. In the end, the results of the numerical solution with the experimental results presented by NASA have been investigated, which indicates that the numerical solution is desirable.

Published in	International Journal of Fluid Mechanics & Thermal Sciences (Volume 5, Issue 2)
DOI	10.11648/j.ijfmts.20190502.11
Page(s)	36-42
Creative Commons	This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited.
Copyright	Copyright © The Author(s), 2019. Published by Science Publishing Group

Keywords

S-Shaped Air Intake, Pressure Drop, Geometry Optimization, Distortion

References

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[2]	Little BH, Trimboli WS (1982) An experimental investigation of S-duct diffusers for high-speed prop-fans. Report/Patent Number: AIAA 82–1123.
[3]	McDill PL, Tolle LI (1983) Analytical design and experimental verification of S-duct diffusers for turboprop installations with an offset gearbox. Report/Patent Number: AIAA PAPER 83–1211.
[4]	Vakili A, Wu JM, Liver P, Bhat MK (1983) Measurements of compressible secondary flow in a circular S-duct Report/Patent Number: AIAA PAPER 83–1739.
[5]	Reichert BA, Wendt BJ (1993) An experimental investigation of S-duct flow controling arrays of low–profile vortex generators. Report/Patent Number: AIAA PAPER 93–18.
[6]	Reichert BA, Wendt BJ (1994) Improving diffusing S-duct performance by secondary flow control. Report/Patent Number: AIAA PAPER 94–0365.
[7]	Lee BJ, Kim C, Rho OH (2003) Aerodynamic optimization for the subsonic S-shaped diffuser using two-equation turbulence models. Report/Patent Number: AIAA PAPER 2003–3960.
[8]	Weng PF, Guo RW (1994) On swirl control in an S-shaped air intake high angle of attack. Report/Patent Number: AIAA PAPER 94–366.
[9]	Mayer DW, Anderson BH, Johnson TA (1998) 3D subsonic diffuser design and analysis. Report/Patent Number: AIAA PAPER 98–3418.
[10]	Silva Lopes A, Piomelli U (2003) Large eddy simulation of the flow in an S-duct. Report/Patent Number: AIAA PAPER 2003–964.
[11]	Pradeep AM, Sullerey RK (2004) Secondary flow control in a circular S-duct diffuser using vortex generator jets. Report/Patent Number: AIAA 2004–2615.
[12]	Stanley R, Mohler Jr (2004) Wind-US flow calculations for the M2129 S-duct using structured and unstructured grids. Report/Patent Number: AIAA 2004–525.
[13]	Jirasek A (2006) Design of vortex generator flow control in inlets. J Aircraft, 43 (6).
[14]	Kirk AM, Rediniotis OK, Cizmas PGA (2007) Numerical and experimental investigation of a serpentine inlet duct. Report/Patent Number: AIAA 2007–842.
[15]	Abdellatif OE, Abd Rabbo M, Abd Elganny M, Shahin I (2008) Area ratio effect on the turbulent flow through a diffusing S-duct using large–eddy simulation. Report/Patent Number: AIAA 2008–5726.
[16]	Zhang JM, Wang CF, Lum KY (2008) Multidisciplinary design of S-shaped intake. AIAA 2008–7060.
[17]	Johnson BC, Webster RS, Sreenivas K (2010) A numerical investigation of S-duct flows with boundary layer ingestion Report/Patent Number: AIAA 2010–841.
[18]	Bayati Morteza, Fathi Mahdi, Bahmani NadAli, Gholami Ali (2007), Aerodynamic design and aerodynamic optimization of engine air intake of a jet drum.
[19]	BehfardShad Qasem, Forghani Farzad (2009), Numerical investigation of total pressure in a S-shaped air intake duct in different Mach numbers, 8th International Aerospace Conference.
[20]	BehfardShad Qasem, Mahlou Saeud, Kadivar Amin (2009), Investigating the effects of the installation of vortex plate and floating-point blown plates on the efficiency of a bending air intake duct, International Aerospace Conference.
[21]	https://www.grc.nasa.gov/WWW/wind/valid/sduct/sduct01/sduct01.html.

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APA Style

Hamid Parhrizkar, Kiumars Khani Aminjan, Mohammad Mahdi Doustdar, Ahad Heydari. (2019). Optimization of S-Shaped Air Intake by Computational Fluid Dynamics. International Journal of Fluid Mechanics & Thermal Sciences, 5(2), 36-42. https://doi.org/10.11648/j.ijfmts.20190502.11

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ACS Style

Hamid Parhrizkar; Kiumars Khani Aminjan; Mohammad Mahdi Doustdar; Ahad Heydari. Optimization of S-Shaped Air Intake by Computational Fluid Dynamics. Int. J. Fluid Mech. Therm. Sci. 2019, 5(2), 36-42. doi: 10.11648/j.ijfmts.20190502.11

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AMA Style

Hamid Parhrizkar, Kiumars Khani Aminjan, Mohammad Mahdi Doustdar, Ahad Heydari. Optimization of S-Shaped Air Intake by Computational Fluid Dynamics. Int J Fluid Mech Therm Sci. 2019;5(2):36-42. doi: 10.11648/j.ijfmts.20190502.11

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@article{10.11648/j.ijfmts.20190502.11,
  author = {Hamid Parhrizkar and Kiumars Khani Aminjan and Mohammad Mahdi Doustdar and Ahad Heydari},
  title = {Optimization of S-Shaped Air Intake by Computational Fluid Dynamics},
  journal = {International Journal of Fluid Mechanics & Thermal Sciences},
  volume = {5},
  number = {2},
  pages = {36-42},
  doi = {10.11648/j.ijfmts.20190502.11},
  url = {https://doi.org/10.11648/j.ijfmts.20190502.11},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijfmts.20190502.11},
  abstract = {Due to the presence of air intakes outside the body of some missiles with research objectives as well as some unmanned aerial, the use of the air intake duct in S-shaped is necessary and therefore the air flow quality must be determined, with the most important parameters being the total drop and distortion is from the beginning of the air intake until the delivery phase to the engine. In this research, it has been determined that the optimum air intake geometry is determined according to the dimensions of a unmanned aerial. Therefore, we first tried to optimize the geometry of S-shaped air intake and then optimize this geometry based on the reduction of total pressure drop. The computational grid with ICEM software and mesh analysis by computational fluid dynamics (Fluent software) has been done. Given that the intake of unmanned aerial was considered in this study, Mach flight is considered 0.3. Since the output section is actually the same section of the motor, whose cross section is constant, it has been considered in optimizing the inlet section and the wall. By optimizing geometry, the total pressure drop dropped to about half. Given the fact that the optimization repetition resulted in undesirable changes in geometry, optimization of geometry was not repeated. Additionally, by comparing the optimized geometry with the initial geometry, It is known that the slow rotation of the flow (the lower rotation angle) reduces the total pressure drop and reduces the amount of distortion. In the end, the results of the numerical solution with the experimental results presented by NASA have been investigated, which indicates that the numerical solution is desirable.},
 year = {2019}
}

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TY  - JOUR
T1  - Optimization of S-Shaped Air Intake by Computational Fluid Dynamics
AU  - Hamid Parhrizkar
AU  - Kiumars Khani Aminjan
AU  - Mohammad Mahdi Doustdar
AU  - Ahad Heydari
Y1  - 2019/06/04
PY  - 2019
N1  - https://doi.org/10.11648/j.ijfmts.20190502.11
DO  - 10.11648/j.ijfmts.20190502.11
T2  - International Journal of Fluid Mechanics & Thermal Sciences
JF  - International Journal of Fluid Mechanics & Thermal Sciences
JO  - International Journal of Fluid Mechanics & Thermal Sciences
SP  - 36
EP  - 42
PB  - Science Publishing Group
SN  - 2469-8113
UR  - https://doi.org/10.11648/j.ijfmts.20190502.11
AB  - Due to the presence of air intakes outside the body of some missiles with research objectives as well as some unmanned aerial, the use of the air intake duct in S-shaped is necessary and therefore the air flow quality must be determined, with the most important parameters being the total drop and distortion is from the beginning of the air intake until the delivery phase to the engine. In this research, it has been determined that the optimum air intake geometry is determined according to the dimensions of a unmanned aerial. Therefore, we first tried to optimize the geometry of S-shaped air intake and then optimize this geometry based on the reduction of total pressure drop. The computational grid with ICEM software and mesh analysis by computational fluid dynamics (Fluent software) has been done. Given that the intake of unmanned aerial was considered in this study, Mach flight is considered 0.3. Since the output section is actually the same section of the motor, whose cross section is constant, it has been considered in optimizing the inlet section and the wall. By optimizing geometry, the total pressure drop dropped to about half. Given the fact that the optimization repetition resulted in undesirable changes in geometry, optimization of geometry was not repeated. Additionally, by comparing the optimized geometry with the initial geometry, It is known that the slow rotation of the flow (the lower rotation angle) reduces the total pressure drop and reduces the amount of distortion. In the end, the results of the numerical solution with the experimental results presented by NASA have been investigated, which indicates that the numerical solution is desirable.
VL  - 5
IS  - 2
ER  -

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Author Information

Hamid Parhrizkar

Faculty of Aerospace Engineering, Malek Ashtar University of Technology, Tehran, Iran
Kiumars Khani Aminjan

Faculty of Aerospace Engineering, Malek Ashtar University of Technology, Tehran, Iran
Mohammad Mahdi Doustdar

Faculty of Engineering, Imam Hossein University, Tehran, Iran
Ahad Heydari

Faculty of Engineering, University of Mohaghegh Ardabili, Ardabil, Iran

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APA Style

Hamid Parhrizkar, Kiumars Khani Aminjan, Mohammad Mahdi Doustdar, Ahad Heydari. (2019). Optimization of S-Shaped Air Intake by Computational Fluid Dynamics. International Journal of Fluid Mechanics & Thermal Sciences, 5(2), 36-42. https://doi.org/10.11648/j.ijfmts.20190502.11

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ACS Style

Hamid Parhrizkar; Kiumars Khani Aminjan; Mohammad Mahdi Doustdar; Ahad Heydari. Optimization of S-Shaped Air Intake by Computational Fluid Dynamics. Int. J. Fluid Mech. Therm. Sci. 2019, 5(2), 36-42. doi: 10.11648/j.ijfmts.20190502.11

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AMA Style

Hamid Parhrizkar, Kiumars Khani Aminjan, Mohammad Mahdi Doustdar, Ahad Heydari. Optimization of S-Shaped Air Intake by Computational Fluid Dynamics. Int J Fluid Mech Therm Sci. 2019;5(2):36-42. doi: 10.11648/j.ijfmts.20190502.11

Copy | Download

@article{10.11648/j.ijfmts.20190502.11,
  author = {Hamid Parhrizkar and Kiumars Khani Aminjan and Mohammad Mahdi Doustdar and Ahad Heydari},
  title = {Optimization of S-Shaped Air Intake by Computational Fluid Dynamics},
  journal = {International Journal of Fluid Mechanics & Thermal Sciences},
  volume = {5},
  number = {2},
  pages = {36-42},
  doi = {10.11648/j.ijfmts.20190502.11},
  url = {https://doi.org/10.11648/j.ijfmts.20190502.11},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijfmts.20190502.11},
  abstract = {Due to the presence of air intakes outside the body of some missiles with research objectives as well as some unmanned aerial, the use of the air intake duct in S-shaped is necessary and therefore the air flow quality must be determined, with the most important parameters being the total drop and distortion is from the beginning of the air intake until the delivery phase to the engine. In this research, it has been determined that the optimum air intake geometry is determined according to the dimensions of a unmanned aerial. Therefore, we first tried to optimize the geometry of S-shaped air intake and then optimize this geometry based on the reduction of total pressure drop. The computational grid with ICEM software and mesh analysis by computational fluid dynamics (Fluent software) has been done. Given that the intake of unmanned aerial was considered in this study, Mach flight is considered 0.3. Since the output section is actually the same section of the motor, whose cross section is constant, it has been considered in optimizing the inlet section and the wall. By optimizing geometry, the total pressure drop dropped to about half. Given the fact that the optimization repetition resulted in undesirable changes in geometry, optimization of geometry was not repeated. Additionally, by comparing the optimized geometry with the initial geometry, It is known that the slow rotation of the flow (the lower rotation angle) reduces the total pressure drop and reduces the amount of distortion. In the end, the results of the numerical solution with the experimental results presented by NASA have been investigated, which indicates that the numerical solution is desirable.},
 year = {2019}
}

Copy | Download

TY  - JOUR
T1  - Optimization of S-Shaped Air Intake by Computational Fluid Dynamics
AU  - Hamid Parhrizkar
AU  - Kiumars Khani Aminjan
AU  - Mohammad Mahdi Doustdar
AU  - Ahad Heydari
Y1  - 2019/06/04
PY  - 2019
N1  - https://doi.org/10.11648/j.ijfmts.20190502.11
DO  - 10.11648/j.ijfmts.20190502.11
T2  - International Journal of Fluid Mechanics & Thermal Sciences
JF  - International Journal of Fluid Mechanics & Thermal Sciences
JO  - International Journal of Fluid Mechanics & Thermal Sciences
SP  - 36
EP  - 42
PB  - Science Publishing Group
SN  - 2469-8113
UR  - https://doi.org/10.11648/j.ijfmts.20190502.11
AB  - Due to the presence of air intakes outside the body of some missiles with research objectives as well as some unmanned aerial, the use of the air intake duct in S-shaped is necessary and therefore the air flow quality must be determined, with the most important parameters being the total drop and distortion is from the beginning of the air intake until the delivery phase to the engine. In this research, it has been determined that the optimum air intake geometry is determined according to the dimensions of a unmanned aerial. Therefore, we first tried to optimize the geometry of S-shaped air intake and then optimize this geometry based on the reduction of total pressure drop. The computational grid with ICEM software and mesh analysis by computational fluid dynamics (Fluent software) has been done. Given that the intake of unmanned aerial was considered in this study, Mach flight is considered 0.3. Since the output section is actually the same section of the motor, whose cross section is constant, it has been considered in optimizing the inlet section and the wall. By optimizing geometry, the total pressure drop dropped to about half. Given the fact that the optimization repetition resulted in undesirable changes in geometry, optimization of geometry was not repeated. Additionally, by comparing the optimized geometry with the initial geometry, It is known that the slow rotation of the flow (the lower rotation angle) reduces the total pressure drop and reduces the amount of distortion. In the end, the results of the numerical solution with the experimental results presented by NASA have been investigated, which indicates that the numerical solution is desirable.
VL  - 5
IS  - 2
ER  -

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