This is the AGARD-A1 axisymmetric
nozzle/afterbody configuration[1] at Mach 0.7, nozzle pressure ratio
of 3. The figures show geometry and Mach contours, boattail pressure,
streamwise velocity and total pressure profiles at the nozzle exit and at two
locations downstream of it. Predictions by the cubic k-e model[2] are
compared to those by the Reynolds-stress closure of Jakirlic and Hanjalic[3]
and to experimental data. The cubic model outperforms the JH
Reynolds-stress closure in predicting the jet spreading rate.
[1] AGARD AR-266, 1986, Report of the Working Group on Aerodynamics of Aircraft
Afterbody.
[2] Goldberg, U., Batten, P., Palaniswamy, S., Chakravarthy, S., and
Peroomian, O., `Hypersonic Flow Predictions Using Linear and
Nonlinear Turbulence Closures', AIAA Journal of Aircraft, Vol. 37,
No. 4, pp. 671-675, 2000.
[3] Jakirlic, S., and Hanjalic, K, 1995, `A Second-Moment Closure for
Non-Equilibrium and Separating High- and Low-Re-Number Flows', 10th
Symposium on Turbulent Shear Flows, Penn. State Univ., Vol. 3.
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