High-order conservative remapping method is developed to improve flow information exchange accuracy of window embedment technology on non-matched grid-block interface with preservation of conservative property and robustness.Remapping methods with various order of accuracy combined with various stencil selection strategy are compared.Constant distribution,linear and quadratic polynomial distributions are tested for reconstruction of conservative variables on interface.Accuracy and efficiency of linear polynomial WENO remapping are balanced well for engineering application.Numerical study of DLR-F4 wing-body configuration with a mending plate patched on the wing is conducted by a in-house developed code NSAWET.A sharp pressure jump brought by the mending plate is predicted.

RANS/LES hybrid methods are developed on the basis of shear stress transport and weakly nonlinear k-ω models with compressible corrections.Supersonic flowfields behind a cylindrical afterbody are investigated to explore rich flow structures and aerodynamic characteristics.Compressible correction shows good agreement with experiment.Results by hybrid methods present detailed and reasonable flow structures,turbulence information and unsteady characteristics.

The Navier-Stokes equations are solved with the second-order LU-SGS-τTS implicit time-stepping method. The sixth-order symmetric TVD scheme with fifth-order WENO interpolation based on Roe is applied to the convection terms. A boundary layer flow around a flat plate, a low speed flow around the Aerospatial A-profile at high incidence and a transonic flow with shock/boundary interaction around RAE2822 airfoil are computed by Baldwin-Lomax and Spalart-Allmaras models with the transition criterion, respectively. The results show that the approaches capture the transition automatically.

A fully implicit Lower-Upper-Symmetric-Gauss-Seidel (LU-SGS) with pseudo time sub-iteration and the modified Jameson's central scheme are applied to solve thin layer Navier-Stokes(N-S) equations with laminar hypothesis and Baldwin-Lomax(B-L) model for the vortical flows around delta wings at high angles of attack (AOA).To validate the codes,a 65 degree swept delta wing is computed in transonic cases,where M_∞=0.85,α=10°,20° and Re=5×10⁶.Then asymmetrical vortex breakdown flows with M_∞=0.3,and Re=1.3×10⁶,at high AOA around an 80° swept delta wing are presented and discussed.The computational results are compared with experimental data available and good agreement is achieved.

Supported by the Science Foundation of China Academy of Engineering Physics under the Grant No.20010660

A newly developed gas-kinetic BGK scheme is further simplified. Numerical tests show that the new simplification not only keeps the advantages of the old scheme, such as its robustness and automatic satisfaction of the entropy condition but also makes the scheme simpler and more efficient.

A finite volume method is presented for the time dependent viscous incompressible flow around an in line oscillating circular cylinder at Reynolds number of 200、855 and 4 000.The N S equations in finite volume form are solved on a moving grid system, based on a time dependent coordinate transformation.To investigate the vortex shedding characteristics behind the circular cylinder and the effects of Reynolds number and other non dimensional parameters such as reduced amplitude and reduced frequency,several numerical schemes have been tested with different amplitudes and frequencies at each Reynolds number.Present numerical results indicate that several types of vortex shedding modes are mainly dependent on the reduced frequency and also the reduced amplitued,which is called synchronization or lock on.