Investigation of the interaction with a high-speed flow of an underexpanded gas jet injected out of the body

DOI: 10.34759/trd-2021-119-05

Аuthors

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

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

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

Abstract

The interaction of injected gas jets with an incoming high-speed flow is one of the most pressing issues today. The use of injected jets for motion control has a significant advantage over mechanical controls, especially with regard to high maneuverability.

Calculations of the gas-dynamic parameters of a high-speed flow near a conical surface at Mach number M_∞=10-17 were carried out with the characteristics of the incoming flow P_∞=79.8 Pa, T_∞=270 K and the parameters of the injected jets T_j=293 K and J=4.95 — the coefficient of penetration of the gas jet into the incoming flow [1,2].

The object of study is a conical surface with gas injection holes located along the generatrix at a distance x/l=0.3, 0.6, 0.9 from the toe.

When analyzing the distribution of the zones of increased pressure in front of the place of injection of the jet and low pressure behind it, it was found that the value of the pressure coefficient with an increase in the Mach number proportionally increases both in the zone of increased and decreased pressure, regardless of the place of injection. The maximum pressure coefficient difference between the zones of high and low pressure is observed during injection at a distance x/l=0.3. In this case, the injected jet interacts with the head shock wave, locally pushing it away from the model. As a result, the p ̅ on the surface before and after the jets is much higher than in other locations of the injection holes.

It was found that an increase in the oncoming velocity leads to an increase in pressure before and after the injected jet. In this case, in front of the injected jet, the pressure increases more significantly than downstream of it. With an increase in the Mach number, the maximum p ̅  shifts closer to the injection site.

The analysis of the efficiency of the action of jets with different variants of arrangement in high-speed flow is carried out. He showed that, while maintaining the parameters of the injected jets constant, an increase in the incoming flow velocity leads to a decrease in the J coefficient, since the pressure gradient at the shock wave increases.

It was found that the magnitude of the Ky increases with an increase in the incoming flow velocity. The maximum is observed when the injected jet is displaced closer to the nose of the model (at М_∞=17), since in this place the injection of the jet is as close as possible to the head shock wave.

The results of numerical experiments correlate well with the results of field experimental studies [2, 19, 20], carried out using the aerodynamic laboratory of the A.F. Mozhaisky MSA and contribute to a more complete study of the effect of high-speed flow on the elements of aircraft.

Keywords:

gas injection, high-speed flow, pressure coefficient, amplification factor

References

1. Volkov K.N., Emel’yanov V.N., Yakovchuk M.S. Prikladnaya mekhanika i tekhnicheskaya fizika, 2015, vol. 56, no. 5 (333), pp. 64 — 75. DOI 10.15372/PMTF20150505

2. Panfilov E.B., Shevchenko A.V., Prilutskii I.K., Snazin A.A. Trudy MAI, 2021, no. 118. URL: http://trudymai.ru/eng/published.php?ID=158212. DOI 10.34759/trd-2021-118-03
3. Shevchenko A.V. Yashkov SA, Zhitnikov T.A. et al. Investigation of the interaction of conical bodies with an supersonic flow at low angles of attack, Journal of Physics: Conference Series, 2020. DOI: 10.1088/1742-6596/1697/1/012241
4. Karagozian A.R. Transverse jets and their control, Progress Energy and Combustion Science, 2010, no. 36 (5), pp. 531 — 553. DOI: 10.1016/j.pecs.2010.01.001
5. Zhong W., Zhang T., Tamura T. CFD Simulation of Convective Heat Transfer on Vernacular Sustainable Architecture: Validation and Application of Methodology, Sustainability, 2019, no. 11 (15), pp. 4231. DOI: 10.3390/su11154231
6. Michalcová V., Lausová L., Kološ I. Numerical modelling of flow around thermally loaded object, MATEC Web of Conferences, 2017, no. 107, pp. 00082. DOI: 10.1051/matecconf/201710700082
7. Hubova O., Veghova I., Kralik J. Experimental and numerical investigation of in-line standing circular cylinders in steady and turbulent wind flow, IOP Conference Series: Materials Science and Engineering, 2019, vol. 603, issue 3, pp. 032008.
8. Seiler F., Gnemmi P., Ende H. et.al. Jet interaction at supersonic cross flow conditions, Shock Waves, 2003, vol. 13, no. 1, pp. 13 — 23. DOI: 10.1007/s00193-003-0189-y
9. Gnemmi P., Adeli R., Longo J. Computational comparisons of the interaction of a lateral jet on a supersonic generic missile, AIAA Atmospheric Flight Mechanics Conference and Exhibit, 18-21 August 2008, Honolulu. DOI: 10.2514/6.2008-6883
10. Landau L.D., Lifshits E.M. Teoreticheskaya fizika. Gidrodinamika (Theoretical physics. Hydrodynamics), Moscow, Nauka, 1986, vol. VI, 736 p.
11. Brandeis J., Gill J. Experimental investigation of super- and hypersonic jet interaction on missile configurations, Journal of Spacecraft and Rockets, 1998, vol. 35, no. 3, pp. 296 — 302. URL: https://doi.org/10.2514/2.3354
12. Kislovskii V.A. Izmenenie sil na poverkhnosti osesimmetrichnogo tela konechnogo razmera v sverkhzvukovom potoke pri vyduve poperechnoi gazovoi strui (Change of forces on the surface of a finite size axisymmetric body in a supersonic flow with an injected transverse gas jet), Doctor’s thesis, Novosibirsk, 2021, 111 p.
13. Borisov A.D. Trudy MAI, 2016, no. 90. URL: http://trudymai.ru/eng/published.php?ID=74721
14. Larina E.V., Kryukov I.A., Ivanov I.E. Trudy MAI, 2016, no. 91. URL: http://trudymai.ru/eng/published.php?ID=75565
15. Kudimov N.F., Safronov A.V., Tret’yakova O.N. Trudy MAI, 2013, no. 70. URL: http://trudymai.ru/eng/published.php?ID=44440
16. Golovkin M.A. Golovkina E.V. Trudy MAI, 2016, no. 90. URL: http://trudymai.ru/eng/published.php?ID=74633
17. Krasnov N.F., Koshevoi V.N., Kalugin V.T. Aerodinamika otryvnykh techenii (Separated flow aerodynamics), Moscow, Vysshaya shkola, 1988, 348 p.
18. Antonov R.V., Grebenkin V.I., Kuznetsov N.P. et al. Organy upravleniya vektorom tyagi tverdotoplevnykh raket: raschet, konstruktivnye osobennosti, eksperiment (Thrust vector controls for solid-propellant rockets: calculation, design features, experiments), Moscow-Izhevsk, NITs Regulyarnaya i khaoticheskaya dinamika, 2006, 552 p.
19. Prokopenko E.A., Shevchenko A.V., Yashkov S.A. et al. Trudy VKA imeni A.F. Mozhaiskogo, 2018, no. 665, pp. 237 — 246.
20. Prokopenko E.A., Shevchenko A.V., Yashkov S.A. Trudy VKA imeni A.F. Mozhaiskogo, 2019, no. 671, pp. 368 — 376.

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