An update method of rans/les perturbation domain for aircraft aerodynamic simulation

A technology of aerodynamic characteristics and update methods, applied in geometric CAD, design optimization/simulation, CAD numerical modeling, etc., can solve the problems that complex flow fields are difficult to apply, and explicit partitioning requires high manual experience, so as to avoid ineffective calculations, complex The effect of strong flow field adaptability and low dependence on artificial experience

Active Publication Date: 2022-01-07
BEIHANG UNIV
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Problems solved by technology

[0004] Aiming at the problems that the existing RANS / LES hybrid method requires high manual experience for explicit partitioning, complex flow fields are difficult to apply, and the two modes of steady RANS and unsteady LES require complex boundary coupling conditions, the present invention proposes a method for simulating the aerodynamic characteristics of aircraft RANS / LES Perturbation Domain Update Method

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  • An update method of rans/les perturbation domain for aircraft aerodynamic simulation
  • An update method of rans/les perturbation domain for aircraft aerodynamic simulation

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Embodiment 1

[0127] This embodiment simulates the dynamic calculation domain defined when the airfoil has a large angle of attack and deep stall flow, such as figure 2 As shown, the unsteady physical time step is 5×10 -5 , the computing grid satisfies y + <1. It can be seen from the figure that the method of the present invention divides the airfoil flow field into an inviscid region, a RANS mode working region and an LES mode working region. Among them, the LES mode working area is the area defined by the LES dynamic domain, including the large separation flow in the upper surface of the airfoil and the wake area in the flow field; the RANS formula working area is the RANS dynamic domain area, including the airfoil The boundary layer region attached to the lower surface near the wall; the inviscid region belongs to the convective dynamic domain, and the terms and variables related to viscosity in the governing equation are not calculated in the numerical simulation. In the numerical ...

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Abstract

The invention discloses a RANS / LES perturbation domain update method for aircraft aerodynamic characteristic simulation. Based on flow parameters such as viscosity coefficient and velocity gradient, dynamic calculation domains of RANS and LES are established to realize dynamic explicit partitioning of the RANS / LES hybrid method. Therefore, while avoiding the non-physical understanding of the "grey area", the RANS / LES hybrid method's dependence on manual experience can be reduced, and its applicability to the flow field around the complex aircraft can be improved; secondly, the unsteady dual time step method and the The solution of the constant time advancing method is unified. By establishing a dynamic calculation domain that increases with the propagation of the disturbance and converges with the solution, the coupling solution of the steady RANS and the unsteady LES is realized, which can not only ensure that there will be no invalid calculations in the numerical simulation, but also Additional boundary condition processing between RANS and LES work areas can be avoided.

Description

technical field [0001] The invention belongs to the technical field of computational fluid dynamics, and in particular relates to a RANS / LES disturbance domain update method for aircraft aerodynamic characteristic simulation. Background technique [0002] Computational fluid dynamics numerical simulation has become one of the indispensable methods in the prediction of aircraft aerodynamic characteristics. When simulating the flow around an aircraft, the turbulent flow, which has a significant impact on the key aerodynamic characteristics of the aircraft, such as aerodynamic force / torque and aerodynamic heating, is the focus and difficulty of the solution. The most mature turbulence numerical simulation method is the Reynolds-averaged turbulence model (RANS), which has the advantages of computational efficiency such as low grid resolution requirements and stable solution to turbulence problems. However, the RANS method has limited simulation accuracy for spatial free turbule...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/23G06F30/28
CPCG06F30/23G06F30/28G06F30/15G06F2111/10Y02T90/00
Inventor 蒋崇文胡姝瑶高振勋许晨豪李椿萱
Owner BEIHANG UNIV
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