Evaluation of the control efforts of the aircrafts gas-dynamic controls in hypersonic flight modes using the IT-1M hypersonic wind tunnel


DOI: 10.34759/trd-2021-118-03

Аuthors

Panfilov E. B.*, Shevchenko A. V.**, Prilytskiy I. K., Snazin A. A.

Mlitary spaсe Aсademy named after A.F. Mozhaisky, Saint Petersburg, Russia

*e-mail: vka@mil.ru
**e-mail: artnetru@yandex.ru

Abstract

Improving the aircrafts aerodynamic characteristics (AC) in a wide range of speeds is a perspective trend especially with significant restrictions imposed on the shape of structural elements is flow and motion control, namely effect on the airflow to restructure its structure in accordance with the required change in AC and other airflow parameters. The most effective method is the gas-dynamic method, implemented in gas-dynamic controls (GDC) (longitudinal and normal injection of a gas jet fr om a body into a hypersonic flow).

On the experimental setup of the aerodynamic laboratory of MSA the A.F. Mozhaisky — the IT-1M hypersonic impulse wind tunnel (HIWT), a series of experiments was carried out (with the parameters of the undisturbed flow: Mach number (M∞ = 17), Reynolds number (Re∞≈1.4 × 104) and pressure (p∞ = 200 Pa)) to determine the aerodynamic characteristics of an aircraft model using GDC.

The feature of HIWT is the ability to obtain experimental data on quasi-stationary processes in a time interval of 50 ms. Working gas — nitrogen (high purity, 1st grade, GOST 9293-74).

When a gas jet is blowing into an incident hypersonic flow, a complex shock-wave structure arises, as evidenced by the experimentally obtained shadow patterns of flow around a body using GDC.

As an indicator of the effectiveness of the use of a GDC with a different location on the model, the amplification factor was selected (K_у=1+ΔY/P_y, wh ere P_y the GDC thrust; ΔY the increment of the normal force due to the presence of an area of increased pressure in the separation flow zone). A comparative analysis of the effectiveness of various combinations of the use of GDC on the aircraft model when moving in hypersonic flight modes is presented.

As a result of a series of experimental studies on the IT-1M wind tunnel, the effectiveness of the usage GDC AC was investigated at hypersonic flight modes. The values of the aerodynamic forces (normal and longitudinal forces, as well as the pitching moment) acting on the aircraft model during hypersonic flight are obtained. It has been shown that the usage GDC significantly improves the main AC of aircraft. The most effective combinations of GDC for the model under study are options 2 and 3 (with J of the jet equal to 4.95 and 8.53) (Figure 8).

Experimental studies carried out with the use of the HIWT aerodynamic laboratory of the MSA named after A.F. Mozhaisky contribute to a more complete study of the behavior of aircraft elements in a hypersonic flow, as well as the verification of existing and newly developed computational codes for aircraft models with GDC.

Keywords:

hypersonic impulse wind tunnel, argon blowing, shock wave, experimental research

References

  1. Shevchenko A.V., Yur’ev A.S., Kashina M.A. Izvestiya Tul’skogo gosudarstvennogo universiteta. Tekhnicheskie nauki, 2020, no. 2, pp. 107 — 113.

  2. Volkov K.N., Emel’yanov V.N., Yakovchuk M.S. Prikladnaya mekhanika i tekhnicheskaya fizika, 2015, vol. 56, no. 5, pp. 789 — 798.

  3. Prokopenko E.A., Shevchenko A.V., Yashkov S.A. Trudy VKA imeni A.F. Mozhaiskogo, 2018, no. 665, pp. 237 — 246.

  4. Krasil’shchikov A.P., Gur’yashkin L.P. Eksperimental’nye issledovaniya tel vrashcheniya v giperzvukovykh potokakh (Experimental studies of bodies of revolution in hypersonic flows), Moscow, Fizmatlit, 2007, 208 p.

  5. Krasnov N.F. Osnovy aerodinamicheskogo rascheta. Trenie i teploperedacha. Upravlenie obtekaniem letatel’nykh apparatov (Fundamentals of aerodynamic calculation. Friction and heat transfer. Aircraft flow control. Textbook), Moscow, Vysshaya shkola, 1984, 264 p.

  6. Lutsenko A.Yu. Stolyarov E.G., Chernukha P.A. Nauchnyi vestnik Moskovskogo gosudarstvennogo tekhnicheskogo universiteta grazhdanskoi aviatsii, 2015, no. 212 (2), pp. 38 — 44.

  7. Sh. Li, Z.G. Wang, W. Huang, J. Liu, Effect of the injector configuration for opposing jet on the drag and heat reduction, Aerospace Science and Technology, 2016, no. 51, pp. 78 — 86. URL: https://doi.org/10.1016/j.ast.2016.01.014

  8. Y. Kim et al. Study on the combined effect of various injection conditions on the drag reduction by a counter-flow jet in supersonic flow, Aerospace Science and Technology, 2019, vol. 98. URL: https://doi.org/10.1016/j.ast.2019.105580

  9. Karagozian A.R. Transverse jets and their control, Progress in Energy and Combustion Science, 2010, no. 36, pp. 531 — 553. DOI: 10.1016/j.pecs.2010.01.001

  10. Golubev M.P., Gol’dfel’d M.A. Pis’ma v Zhurnal tekhnicheskoi fiziki, 2019, vol. 45, no. 1, pp. 50 — 53. DOI: 10.21883/PJTF.2019.01.47158.17517

  11. Seiler F., Gnemmi P., Ende H., Schwenzer M., Meuer R. Jet interaction at supersonic cross flow conditions, Shock Waves, 2003, vol. 13, no.1, pp. 13 — 23.

  12. Huh J., Lee S. Numerical study on jet interaction of flight vehicle with multi-species jet, 2018 AIAA Aerospace Sciences Meeting, 2018. DOI:10.2514/6.2018-1270

  13. Gnemmi P., Seiler F. Interaction of lateral jet with the projectile external flow, AIAA Atmospheric Flight Dynamics Conference, 2000. DOI:10.2514/6.2000-4196

  14. Golovkin M.A., Golovkina E.V. Trudy MAI, 2016, no. 90. URL: http://trudymai.ru/eng/published.php?ID=74692

  15. Tarasenko O.S., Bodryshev V.V., Abashev V.M. Trudy MAI, 2015, no. 83. URL: http://trudymai.ru/eng/published.php?ID=62032

  16. Samokhvalov N.Yu. Trudy MAI, 2014, no. 74. URL: http://trudymai.ru/published.php?ID=49297

  17. Znamenskaya I.A., Gvozdeva L.G., Znamenskii N.V. Metody vizualizatsii v mekhanike gaza (Imaging Techniques in Gas Mechanics), Moscow, MAI, 2001, 57 p.

  18. Smirnova S.I., Pakhov V.V., Stepanov R.P. et al. Trudy MAI, 2014, no. 73. URL: http://trudymai.ru/eng/published.php?ID=48465

  19. Kotov M.A., Kryukov I.A., Ruleva L.B. et al. Inzhenernyi zhurnal: nauka i innovatsii, 2016, no. 9 (57). DOI 10.18698/2308-6033-2016-9-1537

  20. Kotov M.A., Kryukov I.A, Ruleva L.B., Solodovnikov S.I., Surzhikov S.T. Experimental Investigation Of An Aerodynamic Flow Of Geometrical Models In Hypersonic Aerodynamic Shock Tube, AIAA 2013–2931, AIAA Wind Tunnel and Flight Testing Aero II, 2013. DOI: 10.2514/6.2013-2931


    Download

mai.ru — informational site MAI

Copyright © 2000-2024 by MAI

 Вход