Computer Program for Calculation of Separated Turbulent Flows on Axisymmetric Afterbodies including Exhaust Plume Effects
Final rept. 5 Jul 1977-5 Sep 1978
NIELSEN ENGINEERING AND RESEARCH INC MOUNTAIN VIEW CA
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A computer code for a turbulent boundary-layer, inviscid interaction method for axisymmetric configurations of the type used for isolated nozzle afterbody models is presented. The method is applicable to flows with subsonic free streams, including slightly supercritical flows and to bodies with either high pressure exhaust plumes or solid plume simulators. The method consists of an integral boundary-layer and plume-entrainment method and a finite-difference inviscid-flow method which are coupled iteratively through the boundary-layer displacement thickness. Both attached and separated boundary layers can be calculated. An option is provided for calculating two-dimensional boundary layers. The procedure for separated flows is to specify the displacement thickness of the boundary layer and calculate the free-stream velocity distribution from both the boundary-layer equations and the inviscid-flow equations. The separation point location and the angle of the displacement surface are found by an iterative procedure.
- Computer Programming and Software
- Fluid Mechanics
- Jet and Gas Turbine Engines