Axisymmetric afterbody flow separation at transonic speeds in presence of jet exhaust

Mathur, NB and Yajnik, KS (1989) Axisymmetric afterbody flow separation at transonic speeds in presence of jet exhaust. In: 9th International Symposium on Air Breathing Engines, 03-08 Sept 1989, Athens, Greece.

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The separated transonic-interaction characteristics of an axisymmetric boat- tailed afterbody configuration were investigated using a model consisting of an equivalent body of revolution of a representative combat aircraft configuration and a 0.3 trisonic wind tunnel. Experiments were carried out in the free stream Mach number range of 0.98 to 1.21 at constant free stream Reynolds number of 35 x 10 to the 6th/m, keeping the model at 0-deg incidence. Results show that an increase of free stream Mach number in the transonic range caused the separated flow region to move downstream toward the boat-tail end, while an increase in jet pressure ratio caused the upstream movement of the separated flow locations over the boat-tail.

Item Type: Conference or Workshop Item (Paper)
Uncontrolled Keywords: Afterbodies;Boundary layer flow;Jet exhaust;Seperated flow; transonic speed;Boattails;Mach number;Pressure distribution; Pressure ratio;Turbulent boundary layer;Wind tunnel tests
Subjects: AERONAUTICS > Aerodynamics
Division/Department: Experimental Aerodynamics Division, CSIR Centre for Mathematical Modelling and Computer Simulation
Depositing User: shankar sk nadoor
Date Deposited: 03 Nov 2006
Last Modified: 24 May 2010 09:52

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