منابع مشابه
Flow Simulation over Re-Entry Bodies at Supersonic & Hypersonic Speeds
In the present paper, flow simulations are carried on two design configurations of re-entry vehicles, FIRE II and OREX using commercial flow solvers. The purpose of the paper is to present the effect of flight attitude upon the aerodynamic characteristics of an Apollo shaped re-entry capsule. This paper exemplifies the importance of the aerodynamic forces effect on the motion of re-entry vehicl...
متن کاملSimulations of Hypersonic Flow past a Re-entry Capsule Using Dsmc Method
DSMC simulation of re-entry of an object with shape and size close to that of ISRO’s Space Recovery Experiment (SRE) capsule has been analysed using the open-source tool dsmcFoam for three altitude conditions, viz. 85 km, 100 km and 115 km, and for three angles of attack, viz. 0, 20&40. The hypersonic free stream velocity of 8000 m/s and boundary surface temperature of 300 K have been used for ...
متن کاملHypersonic Entry Aeroshell Shape Optimization
Several different approaches to shape optimization are explored to identify hypersonic aeroshell shapes that will increase landed mass capability by maximizing drag-area for a specified lift-to-drag ratio. The most basic approach manipulates standard parameters associated with analytic aeroshell shapes like the sphere-cone and ellipsled. More general approaches manipulate the control points of ...
متن کاملHypersonic Flow
A method for computing inviscid hypersonic ow over complex conngurations using unstructured meshes is presented. The unstructured grid solver uses an edge{based nite{volume formulation. Fluxes are computed using a ux vector splitting scheme that is capable of representing constant enthalpy solutions. Second{order accuracy in smooth ow regions is obtained by linearly reconstructing the solution,...
متن کاملImplicit implementation of material response and moving meshes for hypersonic re-entry ablation
A one-dimensional material response implicit solver with surface ablation and pyrolysis is implicitly coupled to LeMANS, a CFD code for the simulation of weakly ionized hypersonic flows in thermo-chemical non-equilibrium. Following verification and validation of the blowing wall boundary conditions and ablation coupling, the implementation of a moving mesh algorithm in the flow solver is propos...
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ژورنال
عنوان ژورنال: AIAA Journal
سال: 1963
ISSN: 0001-1452,1533-385X
DOI: 10.2514/3.1711