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Advances in Aircraft and Spacecraft Science
  Volume 1, Number 4, October 2014, pages 399-408
DOI: http://dx.doi.org/10.12989/aas.2014.1.4.399
 


Numerical simulations of convergent-divergent nozzle and straight cylindrical supersonic diffuser
R.C. Mehta and G. Natarajan

 
Abstract
    The flowfields inside a contour and a conical nozzle exhausting into a straight cylindrical supersonic diffuser are computed by solving numerically axisymmetric turbulent compressible Navier-Stokes equations for stagnation to ambient pressure ratios in the range 20 to 34. The diffuser inlet-to-nozzle throat area ratio and exit-to-throat area ratio are 21.77, and length-to-diameter ratio of the diffuser is 5. The flow characteristics of the conical and contour nozzle are compared with the help of velocity vector and Mach contour plots. The variations of Mach number along the centre line and wall of the conical nozzle, contour nozzle and the straight supersonic diffuser indicate the location of the shock and flow characteristics. The main aim of the present analysis is to delineate the flowfields of conical and contour nozzles operating under identical conditions and exhausting into a straight cylindrical supersonic diffuser.
 
Key Words
    CFD simulation; supersonic diffuser; compressible flow; nozzle
 
Address
R.C. Mehta : Department of Aeronautical Engineering, Noorul Islam University, Kumaracoil, 629180, Tamil Nadu, India
G. Natarajan : Department of Mechanical Civil Engineering, Kumaracoil, 629180, Tamil Nadu, India
 

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