Heat Flux Computation in Hypersonic Flow with Cartesian Mesh Using Hybrid Solution Methodology

V. Ashok(1*), V. Adimurthy(2), George Joseph(3)

(1) Group Director, Aerodynamics and Aerothermal Group, Vikram Sarabhai Space Centre, Thiruvananthapuram, India
(2) Dean R&D, Indian Institute of Space Science and Technology, Thiruvananthapuram, India
(3) Aeronautics Entity, Vikram Sarabhai Space Centre, Thiruvananthapuram, India
(*) Corresponding author


DOI's assignment:
the author of the article can submit here a request for assignment of a DOI number to this resource!
Cost of the service: euros 10,00 (for a DOI)

Abstract


A hybrid solution methodology has been developed to solve laminar hypersonic flow by starting the solution with a Cartesian mesh Euler solution and then resolving the boundary layer by building prism layers from the wall panels obtained from the Cartesian mesh and performing laminar Navier-Stokes computation for this prism layer after mapping the Cartesian mesh Euler solution on to this prism layer. The solver, developed based on this approach when compared with recent experimental data, predicts the heat flux with good accuracy for a laminar hypersonic flow over typical sphere cone cylinder flare geometry. Since the whole procedure is fully automated, it has a good potential to handle near-wall resolution with a Cartesian mesh for complex geometries as well.
Copyright © 2013 Praise Worthy Prize - All rights reserved.

Keywords


Cartesian Mesh; Heat Flux; Hybrid Solution; Hypersonic Flow

Full Text:

PDF


References


Karman. S.L., SPLITFLOW: - A 3D unstructured Cartesian/prismatic grid CFD code for complete geometries, AIAA Paper No. 95-0343, 1995.

Z. J. Wang,, A fast nested multi-grid viscous flow solver for adaptive Cartesian/Quad grids. International Journal for Numerical Methods in Fluids., 33:657-680, 2000.

Aaron Katz., Antony Jameson and Andrew M Wissink., A Multi-solver scheme for viscous flows using adaptive Cartesian grids and meshless grid communication, AIAA-2009-768.

Xiangying Chen., and Ge-Cheng Zha., A hybrid Cartesian-Body fitted grid approach for simulation of flows in complex geometries, AIAA-2009-3880.

M.D.de Tullio et al., An immersed boundary method for compressible flows using local grid refinement, Journal of Computational Physics, 225, pp 2098-2117, 2007.

Rajat Mittal and Gianluca Iaccarino.,Immersed Boundary methods, Annual Review of Fluid Mechanics, 37:239-61, 2005.

Anvar Gilmanov, Fotis Sotiropoulos., A hybrid Cartesian /immersed boundary method for simulating flows with 3D , geometrically complex moving bodies, Journal of Computational Physics, 2005.

Georgi Kalitzin and Gianluca Iaccarino., Towards immersed boundary simulation of high Reynold number flows, Centre for Turbulence Research, Annual briefs, 2003.

S.Kang., An improved immersed boundary method for computation of turbulent flows with heat transfer”. Ph.D Dissertation, Stanford University, 2008.

Yong Cho et.al., Immersed boundary method for compressible high Reynolds number viscous flow around moving bodies”- AIAA-2007-125.

Ya’eer Kidron et al., Robust Cartesian grid flow solver for high Reynolds number turbulent flow simulations “. AIAA Journal, Vol.48, N0.6, 2010.

V.Ashok and T.C.Babu., Parallelisation of a Navier-Stokes code on a cluster of workstations” Lecture Notes in Computer Science-1745 Ed-Prith Banerjee.,Viktor.K.Prasanna., Bhabani.P.Sinha. Pp-349-353,1999.

Liou. M.S and Stefen,C.J Jr., A new flux splitting scheme, J.Computational Physics,107,pp 23-39, 1993.

E.F.Toro , Riemann Solvers and numerical methods for fluid mechanics: A practical introduction”. Springer Ed, 2009.

Venkatakrishnan.V., Convergence to steady state solutions of the Euler equations on unstructured grids with limiters. J. Computational Physics, 118(1995), pp.120-130, 1995.

Weiss,J.M, Maruszweski,J.P, Smith,W.A., Implicit solution of preconditioned Navier-Stokes equations using algebraic multigrid. AIAA Journal, 37, pp-29-36, 1999.

Shigeru Kuchi-Ishi et al.. Comparative Force/Heat-flux measurements between JAXA hypersonic test facilities using standard model HB-2 (Part-1: 1.27m Hypersonic Wind Tunnel Results), JAXA-RR-04-035E- March-2005.


Refbacks

  • There are currently no refbacks.



Please send any question about this web site to info@praiseworthyprize.com
Copyright © 2005-2020 Praise Worthy Prize