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Computation of accurate and efficient numerical results for space vehicle design and analysis is a challenging task because it takes large computational time to predict complex flow physics of space vehicle. Space vehicle travels through continuum as well as rarefied region during flight. Continuum region aerodynamics can be predicted by solving Navier Stokes equation. Explicit schemes require low computational hardware facility but increase computational time by limiting time step to a certain limit defined by stability criteria. An extensive research is being done for last three decades to overcome this stability restriction. Initially, Harten proposed a large time step Total Variation Diminishing (TVD) second order accurate (2K+3) point scheme with explicit formulation under a CFL restriction of K. Harten’s developed large time step scheme and its modified Qian’s form have been tested with minmod limiter extensively. However detailed analysis of these schemes with more compressive limiter is still in progress. Present research investigates Qian’s modified large time step scheme behavior with compressive limiters for complex flow physics. Shock tube problem with Lax boundary condition is computed to point out advantages and short comings of Qian’s proposed modified scheme
Noor Fatima Siddiqui, Asif Raza Khan, Mukkarum Hussain. (2019) Computation of LAX Shock Tube Test Case through Large Time Step Scheme with Compressive Limiters, , Proc. of the PAS: A; 56, Issue 1.
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