Navier-Stokes and Experimental Modeling of Blunt-Base Rocket Nozzle Flow

  • C. K. Forester
  • I. Strom
Conference paper
Part of the International Union of Theoretical and Applied Mechanics book series (MANUTECH)


The influence of grid placement and grid density on the ability to compute an underexpanded jet in a supersonic afterbody flowfield is studied using a conservation-based body-fitted computational technique. The thin-shear-layer formulation of the compressible, Reynolds-averaged, Navier-Stokes equations together with mass and energy conservation equations are modeled using an artificial time-dependent, explicit numerical algorithm with the turbulence approximated by a two-layer algebraic model with wall functions for the solid boundaries and whose properties are tailored to the three physically distinct mixing zones. Solutions are obtained for supersonic flow over an axisymmetric conical afterbody with a blunt base, containing a centered propulsive jet where the freestream Mach number is 2.0 and the jet exit Mach number is 2.5. Exhaust exit-plane static pressures are considered in the range of one to nine times the freestream static pressure. The conical nozzle-exit half-angles are zero and twenty degrees. Comparisons are made between computed and experimental results for base pressure, separation length, afterbody pressure distribution, and flowfield structure. The numerical solutions are found to be sensitive to the computational grid structure and the mixing (turbulence) model. Error norms are applied to aid the detection of inappropriate grid choices. The best results are obtained with adaptive grids that track both free shear layers and a mixing model which is germain to the local flow features.


Mach Number Computational Region Local Truncation Error Nozzle Flow Nozzle Pressure Ratio 
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  1. 1.
    Wagner, N. and L. E. Putnam (Eds.), “Comparison of Experimental and Computational Modeling of Boattail/Nozzle Flow,” AGARD WG-08, 1985.Google Scholar
  2. 2.
    Putnam, L. E. and Bissinger, N. C., “Results of AGARD Assessment of Prediction Capabilities for Nozzle Afterbody Flows,” AIAA paper 85-1464.Google Scholar
  3. 3.
    Deiwert, G. S., “Supersonic Axisymmetric Flow Over Boattails,” AIAA Journal, Vol 22, pp. 1358–1365, 1984.CrossRefMATHADSGoogle Scholar
  4. 4.
    Petrie, H. L. and Walker, B. J., “Comparison of Experiment and Computation for a Missile Base Region Flowfield with a Centered Propulsive Jet,” AIAA paper 85-1618.Google Scholar
  5. 5.
    Agrell, J. and R. A. White, “An Experimental Investigation of Supersonic Axisymmetric Flow over Boattails Containing a Centered Propulsive Jet,” The Aeronautical Research Institute of Sweden, Stockholm, Tech. Note AU-913, 1979.Google Scholar
  6. 6.
    Birch, S. F., private communication, 1985.Google Scholar
  7. 7.
    Forester, C. K., “Error Norms for the Adaptive Solution of the Navier-Stokes Equations,” NASA Langley Research Center Report NASA CR-165 828, under cotract NASI-16408, May 1982.Google Scholar
  8. 8.
    Forester, C. K. “Numerical Simulation of the Interaction of Jet and Freestream Flows in Engine Exhaust Systems,” AIAA paper 78-144, presented at AIAA 16th Aerospace Sciences Meeting, Huntsville, Alabama, Jan. 16–18, 1978Google Scholar
  9. 9.
    Peery, K. M. and C. K. Forester, “Numerical Simulation of Multistream Nozzle Flows,” AIAA Paper 79-1549, 1979.Google Scholar
  10. 10.
    Forester, C. K., “Error Norm Guided Flow Analysis,” Report #1, AFOSR Contract No. F49620-84-C-0037, April 1985.Google Scholar

Copyright information

© Springer-Verlag Berlin, Heidelberg 1986

Authors and Affiliations

  • C. K. Forester
    • 1
  • I. Strom
    • 1
  1. 1.Boeing Military Airplane Co.SeattleUSA

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