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.Full text not available from this repository.
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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