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Evaluation of fluidic thrust vectoring nozzle via thrust pitching angle and thrust pitching moment

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Abstract

Shock vector control (SVC) in a converging–diverging nozzle with a rectangular cross-section is discussed as a fluidic thrust vectoring (FTV) method. The interaction between the primary nozzle flow and the secondary jet is examined using experiments and numerical simulations. The relationships between FTV parameters [nozzle pressure ratio (NPR) and secondary jet pressure ratio (SPR)] and FTV performance (thrust pitching angle and thrust pitching moment) are investigated. The experiments are conducted with an NPR of up to 10 and an SPR of up to 2.7. Numerical simulations of the nozzle flow are performed using a Navier-Stokes solver with input parameters set to match the experimental conditions. The thrust pitching angle and moment computed from the force-moment balance are used to evaluate FTV performance. The experiment and numerical results indicate that the FTV parameters (NPR and SPR) directly affect FTV performance. Conventionally, FTV performance evaluated by the common method using thrust pitching angle is highly dependent on the location of evaluation. Hence, in this study, we show that the thrust pitching moment, a parameter which is independent of the location, is the appropriate figure of merit to evaluate the performance of FTV systems.

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References

  1. Taylor, J.G.: A Static investigation of a simultaneous pitch and yaw thrust vectoring 2-D C-D nozzle. AIAA 88-2998 (1988)

  2. Asbury, S.C., Capone, F.J.: Multiaxis thrust-vectoring characteristics of a model representative of the F-18 high-alpha research vehicle at angles of attack from \(0^{\circ }\) to \(70^{\circ }\). NASA TP-3531 (1995)

  3. Deere, K.A.: Summary of fluidic thrust vectoring research conducted at NASA Langley research center. AIAA 2003-3800 (2003)

  4. Chiarelli, C., Johnsen, R.K., Shieh, C.F.: Fluidic scale model multi-plane thrust vector control test results. AIAA 93-2433 (1993)

  5. Deere, K.A.: PAB simulations of a nozzle with fluidic injection for yaw thrust-vector control. AIAA 98-3254 (1998)

  6. Federspiel, J., Bangert, L., Wing, D.J., Hawkes, T.: Fluidic control of nozzle flow-some performance measurements. AIAA 95-2605 (1995)

  7. Deere, K.A., Berrier, B.L.: Computational study of fluidic thrust vectoring using separation control in a nozzle. AIAA 2003-3803 (2003)

  8. Wing, D.J., Giuliano, V.J.: Fluidic thrust vectoring of an axisymmetric exhaust nozzle at static conditions. FEDSM 97-3228 (1997)

  9. Mason, M.S., Crowther, W.J.: Fluidic thrust vectoring of low observable aircraft. AIAA 2004-2210 (2004)

  10. Sobester, A., Keane, A.J.: Multi-objective optimal design of a fluidic thrust vectoring nozzle. AIAA 2006-2916 (2006)

  11. Waithe, K.A., Deere, K.A.: Experimental and computational investigation of multiple injection ports in a convergent-divergent nozzle for fluidic thrust vectoring. AIAA 2003-3802 (2003)

  12. Flamm, J.D., Deere. K.A., Mason, M.L., Berrier, B.L., Johnson, S.K.: Experimental study of an axisymmetric dual throat fluidic thrust vectoring nozzle for supersonic aircraft application. AIAA 2007-7084 (2007)

  13. Zmijanovic, V., Lago, V., Sellam, M., Chpoun, A.: Thrust shock vector control of an axisymmetric conical supersonic nozzle via secondary transverse gas injection. Shock Waves 24, 97–111 (2014)

    Article  Google Scholar 

  14. Li, L., Saito, T.: Numerical and experimental investigations of fluidic thrust vectoring mechanism. Int. J. Aerosp. Innov 4(1–2), 53–64 (2012)

    Article  Google Scholar 

  15. Blake, B.A.: Numerical investigation of fluidic injection as a means of thrust modulation. Final Thesis Report, University of New South Wales, Australia (2009)

  16. Li, L., Saito, T.: A survey of performance of fluidic thrust vectoring mechanisms by numerical and experimental studies. Int. J. Aerosp. Innov 5(3+4), 51–60 (2013)

    Article  Google Scholar 

  17. Anderson, D.A., Tannehill, J.C., Pletcher, R.H.: Computational Fluid Mechanics and Heat Transfer. Hemisphere Publishing Corporation, New York (1984)

  18. Yoon, S., Jameson, A.: Lower-upper symmetric-Gauss-Seidel method for the Euler and Navier-Stokes equations. AIAA J 26(9), 1025–1026 (1988)

    Article  Google Scholar 

  19. Liou, M.S.: A sequel to AUSM, Part II: AUSM+-up for all speeds. J. Comput. Phys 214(1), 137–170 (2006)

    Article  MATH  Google Scholar 

  20. Van Leer, B.: Towards the ultimate conservation difference scheme. IV. A new approach to numerical convection. J. Comput. Phys 23(3), 276–299 (1977)

    Article  MATH  Google Scholar 

  21. Saito, T., Takayama, K.: Numerical simulations of nozzle starting process. Shock Waves 9, 73–79 (1999)

    Article  MATH  Google Scholar 

  22. Hirota, M., Saito, T., Kawauchi, M.: Important factors in the starting process of a two-dimensional nozzle. Int. J. Aerosp. Innov 3(4), 207–216 (2011)

    Article  Google Scholar 

  23. Bechwith, I.E., Chen, F.J., Malik, M.R.: Design and fabrication requirements for low-noise supersonic/hypersonic wind tunnels. AIAA 88-0143 (1988)

  24. Gruber, M.R., Goss, L.P.: Surface pressure measurement in supersonic transverse injection flowfields. J. Propuls. Power 15, 633–641 (1999)

    Article  Google Scholar 

  25. Zukoski, E.E., Spaid, F.W.: Secondary injection of gases into a supersonic flow. AIAA J 2, 1689–1696 (1964)

    Article  Google Scholar 

  26. Billig, F.S., Orth, R.C., Lasky, M.: A unified analysis of gaseous jet penetration. AIAA J 9, 1048–1057 (1971)

    Article  Google Scholar 

  27. Cohen, L.S., Coulter, L.J., William, J.E.: Penetration and mixing of multiple gas jets subjected to a cross flow. AIAA J 9, 718–724 (1971)

    Article  Google Scholar 

  28. Takahashi, H., Oso, H., Kouchi, T., Masuya, G., Hirota, M.: Scalar spatial correlations in a supersonic mixing flowfield. AIAA J 48(2), 443–452 (2010)

    Article  Google Scholar 

  29. Takahashi, H., Masuya, G., Hirota, M.: Effects of injection and main flow conditions on supersonic turbulent mixing structure. AIAA J 48(8), 1748–1756 (2010)

    Article  Google Scholar 

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Acknowledgments

This work was sponsored by the Scientific Research Foundation for Returned Overseas Chinese Scholars, State Education Ministry, and by the Ministry of Education, Culture, Sports, Science and Technology (MEXT) Grant-in-Aid for Scientific Research (C), No. 21560162. It was also supported by the cooperative research program of the Earthquake Research Institute, the University of Tokyo, Japan. The CFD code “FaSTAR” was developed by the Japan Aerospace Exploration Agency (JAXA).

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Authors and Affiliations

  1. Dalian Jiaotong University, No. 794 Huanghe Road, Shahekou District, Dalian, 116028, China

    L. Li

  2. Muroran Institute of Technology, 27-1 Mizumoto-cho, Muroran, Hokkaido, 050-8585, Japan

    M. Hirota, K. Ouchi & T. Saito

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  1. L. Li
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  2. M. Hirota
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  3. K. Ouchi
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  4. T. Saito
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Corresponding author

Correspondence to M. Hirota.

Additional information

Communicated by R. Bonazza.

This paper is based on work that was presented at the 29th International Symposium on Shock Waves, Madison, Wisconsin, USA, July 14–19, 2013.

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Li, L., Hirota, M., Ouchi, K. et al. Evaluation of fluidic thrust vectoring nozzle via thrust pitching angle and thrust pitching moment. Shock Waves 27, 53–61 (2017). https://doi.org/10.1007/s00193-016-0637-0

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  • DOI: https://doi.org/10.1007/s00193-016-0637-0

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