Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
권호 표지

Study of Flowfield of the Interaction of Secondary Sonic Jet into a Supersonic Nozzle

음속 이차유동 분출시 나타나는 초음속 노즐 내부 유동장에 관한 연구

  • 고현 (연세대학교 대학원 기계공학과) ;
  • 이열 (한국항공대학교 항공우주 및 기계공학부) ;
  • 윤웅섭 (연세대학교 기계공학과)
  • Published : 2003.09.01
Download PDF
⟨ Previous Next ⟩

Abstract

Detailed flowfield resulting from the secondary sonic gas injection into a divergent section of supersonic conical nozzle has been numerically investigated. The three-dimensional flowfield associated with the bow-shock/boundary-layer interaction inside the nozzle has been solved by Reynolds-averaged Navier-Stokes equations with an algebraic and $\kappa$-$\varepsilon$ turbulence model. The numerical results have been compared with the experimental results for the identical flow conditions, and it is shown that the comparison is satisfactory Effects of different injection pressures of the secondary jet on the shock/boundary-layer interactions and the overall flow structure inside the nozzle have been investigated. The vortex structures behind the shock interaction and wall pressure variations have also been studied.

원추형 초음속 노즐 확산부에 이차유동이 음속으로 분출될 때 나타나는 노즐 내부 유동장에 대한 수치적 연구가 이루어졌다. 대수-난류모델과 $\kappa$-$\varepsilon$ 모델을 사용한 레이놀즈-평균 Navier-Stokes 방정식을 계산함으로서 노즐 내부에서 나타나는 충격파와 경계층의 간섭에 의한 3 차원 유동장을 해석하였다. 얻어진 수치해석의 결과는 동일한 조건에서 수행된 실험결과와 잘 일치하고 있음이 판명되었다. 이차유동의 분출압력 변화가 충격파와 경계층의 간섭과 함께 노즐내부 유동장 구조에 미치는 영향을 평가하였다. 아울러 충격파 간섭 후방에서 나타나는 와류유동 구조와 벽면 압력분포에 관한 정보를 얻었다.

Keywords

References

  1. Hawkes, T., 'Computational Analysis of an Axisymmetric Fluidic Injection Nozzle," AIAA paper 96-0116, 1996
  2. Schetz, J. A., and Billig, F. S., 'Penetration ofGaseous Jets Injected into a SupersonicStream,' Journal of Spacecraft and Rocket, Vol. 3, No. 11, Nov., 1996, pp. 1658-1685
  3. Masuya G., 1977, 'Secondary Gas Injection Into a Supersonic Conical Nozzle', AIAA Journal, Vo1.15, No.3, 1977, pp. 301-302 https://doi.org/10.2514/3.63234
  4. Mayes, R. B., Thomas, R. H., and Schetz, J. A., 'Low Angle Injection Into a Supersonic Flow,' AIAA 89-2461, 1989
  5. Balu R., 'Analysis of Performance of a Hot Gas Injection Thrust Vector Control System', Journal of Propulsion and Power, Vol. 7, No. 4, 1991, pp. 580-585 https://doi.org/10.2514/3.23365
  6. Dhinagaran, R., and Bose, T.K., 'Comparison of Euler and Navier-Stokes Solutions for Nozzle Flows with Secondary Injection,' AIAA paper 96-0453, 1996
  7. Ko, H. and Yoon, W.-S., 'Performance Analysis of Secondary Gas Injection into a Conical Rocket Nozzle,,' Journal of Propulsion and Power, Vol. 18, No. 3, 2002, pp. 585-591 https://doi.org/10.2514/2.5972
  8. Sakar, S., Erlebacher, G., Hussaini, M.Y., and Kreiss, H.O., 'The Analysis and Modeling of Dilatational Terms in Compressible Turbulence,' NASA CR 181959, 1989
  9. Baldwin, B.S., and Lomax, H., 'Thin Layer Approximation and Algebraic Model for Separated Flow,' AIAA paper 78-257, 1978
  10. Chien, K.-Y., 'Predictions of Channel and Boundary-Layer Flows with a Low-Reynolds Number Turbulence Model,' AIAA Journal, Vol. 20, No. 1, 1982, pp. 33-38 https://doi.org/10.2514/3.51043
  11. Beam, R.M., and Warming, R.F., 'An Implicit Factored Scheme for the Compressible Navier-Stokes Equations,' AIAA journal, Vol. 16, No. 4, 1978, pp. 393-402 https://doi.org/10.2514/3.60901
  12. Garrison T. J., and Settles, G. S., 'Flowfield Visualization of Crossing Shock-Wave Boundary-Layer Interactions,' AIAA paper 92-0750, 1992