Computational study of reynolds number influence on the oval fixed-geometry air inlet perfomance


Аuthors

Novogorodtsev E. V.*, Koltok N. G.**, Karpov E. V.***

Central Aerohydrodynamic Institute named after N.E. Zhukovsky (TsAGI), 1, Zhukovsky str., Zhukovsky, Moscow Region, 140180, Russia

*e-mail: novogorodtseve91@mail.ru
**e-mail: nikitakoltok@gmail.com
***e-mail: e-karpov@list.ru

Abstract

The purpose of this research is to study the Reynolds number value effect on the flow-around characteristics and characteristics of the isolated air intake. The object of the study is a non-regulated air intake of external air compression with ovoid inlet. The air inlet is equipped with a boundary layer control system, in the form of perforation on the shell braking and trimming surface.

The air intake flow-around numerical simulation was executed based on the solution of the Reynolds-averaged Navier-Stokes equations with the SST turbulence model (RANS-SST approach), using unstructured computational meshes built in the flow areas outside and inside the air intake. Simulation of the air intake duct throttling was performed using the active disk method. The air intake flow-around was modeled at the Re number values ranging from Re ~ 3.8х106 to Re ~ 4.2х107.

The air intake throttling characteristics were obtained on all studied modes by the results of the numerical modeling. The article also presents the Mach number fields in the longitudinal vertical section of the air intake duct and the total pressure recovery coefficient (ν) fields in the duct cross section, corresponding to the engine compressor inlet.

The obtained results analysis revealed a number of specifics of the air inlet throttling characteristics stipulated by the Re number value. Firstly, the value of the ν coefficient increases with an increase the Re number value at the supercritical operating modes of the air intake. The maximum increase of the ν coefficient value was of Δν ≈ 0.01. The ν coefficient value increased due to the decrease of the boundary layer thickness in the air intake duct.

Secondly, the ν coefficient values change slightly with a change in the Re number one the critical operating mode of the air intake.

Thirdly, in subcritical operation conditions of the air intake, the ν coefficient value decreases with an increase of the Re number value. Maximum decrease of the ν coefficient value was Δν ≈ 0.01. The decrease of the ν coefficient value is associated with the losses reduction effect weakening of the flow total pressure in the λ-structure, which occurs while the boundary level control system perforation flow-around.

Fourth, it was revealed that the Re number in the studied values range, did not significantly affect the air intake characteristics by the ¯Δδо parameter.

Further study of the Re number value effect on the characteristics of supersonic air intakes supposes performing numerical studies on the flow-around and characteristics of the air intakes in the layout with the fuselage of prospective civil supersonic aircraft at various Re numbers, as well as conducting tests of the air intakes models at various Re numbers.

Keywords:

air inlet computational fluid dynamics, Reynolds number, geometry-fixed external compression inlet, total pressure recovery coefficient, inlet throttle characteristics

References

  1. Novogorodtsev E.V., Karpov E.V., Koltok N.G. Aerospace MAI Journal, 2021, vol. 28, no. 4, pp. 7-27.

  2. Sun Y., Smith H. Review and prospect of supersonic business jet design, Progress in Aerospace Sciences, 2017, vol. 90. pp. 12-38. DOI: 10.1016/j.paerosci.2016.12.003

  3. Kopiev V.F. et al. On the Fundamental Possibility of a Supersonic Civil Aircraft to Comply with ICAO Noise Requirements Using Existing Technologies, Aerospace, 2022, vol. 9, no. 4, pp. 187. DOI: 10.3390/aerospace9040187

  4. Berton J.J. et al. Supersonic technology concept aeroplanes for environmental studies. AIAA Scitech 2020 Forum, 2020. DOI: 10.2514/6.2020-0263

  5. Furukawa T., Makino Y. Conceptual design and aerodynamic optimization of silent supersonic aircraft at JAXA, 25th AIAA Applied Aerodynamics Conference, 2007. DOI: 10.2514/6.2007-4166

  6. Proskurov S. et al. Installed Fan Noise Simulation of a Supersonic Business Aircraft, Aerospace, 2023, vol. 10, no. 9. DOI: 10.3390/aerospace10090773

  7. Vinogradov V.A., Mel'nikov Ya.A., Stepanov V.A. Uchenye Zapiski TsAGI, 2015, vol. XLVI, no. 2, pp. 26-40.

  8. Vinogradov V.A., Mel'nikov Ya.A., Stepanov V.A. Uchenye zapiski TsAGI, 2017, vol. XLVIII, pp. 24-38.

  9. Watanabe Y., Ueno A., Murakami A. Design of top mounted supersonic inlet for silent supersonic technology demonstrator S3TD, 27th Congress of the International Council of the Aeronautical Sciences, ICAS, 2010, vol. 4, no. 2, pp. 2010.

  10. Babulin A.A., Bol'shunov K.Yu. Trudy MAI, 2012, no. 51. URL: https://trudymai.ru/eng/published.php?ID=29088

  11. Ignatkin Yu.M., Konstantinov S.G. Trudy MAI, 2012, no. 57. URL: https://trudymai.ru/eng/published.php?ID=30875

  12. Makhrov A.S., Pirogov S.Yu. Trudy MAI, 2012, no. 58. URL: https://trudymai.ru/eng/published.php?ID=31045

  13. Kraev V.M., Yanyshev D.S. Trudy MAI, 2010, no. 37. URL: https://trudymai.ru/eng/published.php?ID=13411

  14. Karpov E.V., Koltok N.G., Novogorodtsev E.V. XLIV akademicheskie chteniya po kosmonavtike, Moscow, Izd-vo MGTU im. N.E. Baumana, 2020, vol. 1, pp. 354–355.

  15. Koltok N.G. XLVI Mezhdunarodnaya molodezhnaya nauchnaya konferentsiya «Gagarinskie chteniya-2020», Moscow, Izd-vo MAI, 2020, pp. 161–162.

  16. Pirogov S.Yu., Yur'ev A.S., Tipaev V.V., Makhrov A.S. Aerospace MAI Journal, 2009, vol. 1, no. 3, pp. 27-34.

  17. Rakhmanin D.A., Karpov E.V., Rakhmanina V.E. Aerospace MAI Journal, 2023, vol. 30, no. 2, pp. 35-45.

  18. Karpov E.V., Koltok N.G., Novogorodtsev E.V. Aerokosmicheskie tekhnologii: Sbornik tezisov 62-i Vserossiiskoi nauchnoi konferentsii MFTI, Moscow, MFTI, 2019, pp. 290–292.

  19. Tan H.J., Guo R.W. Design and wind tunnel study of a top-mounted diverterless inlet, Chinese Journal of Aeronautics, 2004, vol. 17, no. 2. pp. 72-78. DOI: 10.1016/S1000-9361(11)60217-3

  20. Bridges J.E., Wernet M.P. PIV measurements of a low-noise top-mounted propulsion installation for a supersonic airliner, AIAA Scitech 2019 Forum, 2019, pp. 0252.

  21. Garbaruk A.V., Strelets M.Kh., Shur M.L. Modelirovanie turbulentnosti v raschetakh slozhnykh techenii (Turbulence modeling in calculations of complex flows), Saint Petersburg, Izd-vo Politekhnicheskogo universiteta, 2012, 88 p.

  22. Reinol’ds O. Dinamicheskaya teoriya dvizheniya neszhimaemoi zhidkosti I opredelenie kriteriya. In: Problemy turbulentnosti: Sbornik perevodnykh statei. Moscow - Leningrad, ONTI, 1936, pp. 135–227.

  23. Anisimov K.S. Kombinirovannyi algoritm opredeleniya aerodinamicheskikh kharakteristik s tsel'yu optimizatsii vozdukhozabornikov dozvukovykh letatel'nykh apparatov (Combined algorithm for determining aerodynamic characteristics in order to optimize the air intakes of subsonic aircraft), Doctor's thesis, Zhukovskii, 2017, 177 p.

  24. Shchepanovskii V.A., Gutov B.I. Gazodinamicheskoe konstruirovanie sverkhzvukovykh vozdukhozabornikov (Gas-dynamic design of supersonic air intakes), Novosibirsk, Nauka, 1993, 224 p.

  25. Menter F.R. Zonal two-equation k-ω turbulence models for aerodynamic flows, 23rd Fluid Dynamics, Plasmadynamics, and Lasers Conference, July 1993, Orlando, FL, U.S.A. DOI: 2514/6.1993-2906

  26. Byushgens G.S. Aerodinamika, ustoichivost' i upravlyaemost' sverkhzvukovykh samoletov (Aerodynamies, stability and contrullability of supersonic aircraft), Moscow, Nauka, Fizmatlit, 1998, 816 p.

  27. Abramovich G.N. Prikladnaya gazovaya dinamika (Applied gas dynamics), Moscow, Nauka, 1976, 888 p.


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