跨流域高超声速绕流Boltzmann模型方程并行算法

doi:10.7527/S1000-6893.2014.0219

Abstract

Abstract:

The unified equation on the molecular velocity distribution function is presented for describing complex hypersonic flow transport phenomena covering various flow regimes by the computable model of Boltzmann collision integral. The discrete velocity ordinate method is used to discretize and reduce velocity space dimensionality of the velocity distribution function, and the gas-kinetic numerical schemes of coupling iteration are constructed directly to solve the molecular velocity distribution function. The computing models of hypersonic aerothermodynamics for the complex vehicles are developed by the evolution and updating based on the molecular velocity distribution function. The new parallel strategy of the gas-kinetic numerical algorithm is established by using the parallelizing technique of domain decomposition with the analysis from variable dependency relations, data communication and parallel expansibility. The data parallel distribution and parallel implementation are researched, the large-scale parallel program design is carried out and then the high-performance parallel algorithm has been established to simulate the hypersonic flow problems around complex vehicles covering various flow regimes, which can run stably in the tens of thousands of CPU or more scale. The hypersonic aerothermodynamics problems from high rarefied transition to continuum flow regimes around three-dimensional sphere-cone satellite body and complex wing-body combination shape with various Knudsen numbers, different Mach numbers, and diverse flying of angles have been computed and verified in high-performance computer with massive scale parallel. The computed results are found in high resolution of the flow fields and good agreement with the related reference experimental data, direct simulation Monte Carlo (DSMC) and theoretical predictions, and the hypersonic complex flow mechanism and changing laws are revealed. It is probably practical that the applying research approaches of the gas-kinetic unified algorithm can be provided to simulate complex hypersonic flow problems covering the whole of flow regimes.

Key words: hypersonic vehicles, covering various flow regimes, aerothermodynamics, Bolztamnn model equation, discrete velocity oridinate method, gas-kinetic unified algorithm, parallel computation

CLC Number:

V411.3

LI Zhihui, WU Junlin, JIANG Xinyu, MA Qiang. A massively parallel algorithm for hypersonic covering various flow regimes to solve Boltzmann model equation[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(1): 201-212.

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A massively parallel algorithm for hypersonic covering various flow regimes to solve Boltzmann model equation

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