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Background: Upregulation of Stathmin 1 (STMN1), a cytoplasmic phosphoprotein that controls the dynamics of cellular microtubules, is linked to malignant behavior and poor prognosis in a range of malignancies. However, little research has been done on STMN1's potential role in HCC as a single factor in DNA methylation, m6A, or immunological modulation. Results: STMN1 is overexpressed in hepatocellular carcinoma, where it is related to clinicopathological parameters and affects the prognosis of HCC patients. STMN1 overexpression plays an important role in the diagnosis and prognosis of hepatocellular carcinoma. Meanwhile, methylation of 7 CpG sites of STMN1 in HCC was correlated with prognosis, and STMN1 expression was closely related to m6A modification. In addition, STMN1 expression is associated with immune cell infiltration, immune molecules, and immune checkpoints in HCC. Conclusion: STMN1 has a significant role in hepatocellular carcinoma diagnosis and prediction. STMN1 is implicated not just in the onset and course but also in the immunological modulation of the disease. DNA methylation and m6A are both linked to STMN1. Therefore, STMN1 could be used as a diagnostic and prognostic biomarker for HCC, as well as a target for immunotherapy. [ABSTRACT FROM AUTHOR]

The assembly of overlapping grids is a key technology to deal with the relative motion of multi-bodies in computational fluid dynamics. However, the conventional implicit assembly techniques for overlapping grids are often confronted with the problem of complicated geometry analysis, and consequently, they usually have a low parallel assembly efficiency resulting from the undifferentiated searching of grid nodes. To deal with this, a parallel implicit assembly method that employs a two-step node classification scheme to accelerate the hole-cutting operation is proposed. Furthermore, the aforementioned method has been implemented as a library, which can be conveniently integrated into the existing numerical simulators and enable efficient assembly of large-scale multi-component overlapping grids. The algorithm and relevant library are validated with a seven-sphere configuration and multi-body trajectory prediction case in the aspects of parallel computing efficiency and interpolation accuracy. [ABSTRACT FROM AUTHOR]

A framework of numerical formulations for the aeroelastic analysis of helicopter rotor is presented in this paper. The blade structural dynamics are modeled by an open source multibody dynamic software MBDYN, which solves finite element equation of elastic bodies in general motions. Then the structural deformation is transformed to blade surface grid by radial base function (RBF) interpolation, and volume grids are regenerated by RBF and TFI methods. Lastly, the fluid governing equations are solved. By integrating the above methods, S76 hovering rotors are simulated and compared to the test data. Results show that elastic torsion decreases local angle of attack. For status at M tip = 0. 6 5 and 𝜃 > 1 0 0 , the shock and shock-induced separation are reduced on the outboard blade, which has remarkable effects on the prediction of rotor hovering performance. [ABSTRACT FROM AUTHOR]

Implicit LU-SGS time integration algorithm has been widely used in parallel computation in spite of its lack of information from adjacent domains. When applied to parallel computation of hovering rotor flows in a rotating frame, it brings about convergence issues. To remedy the problem, three LU factorization-based implicit schemes (consisting of LU-SGS, DP-LUR and HLU-SGS) are investigated comparatively. A test case of pure grid rotation is designed to verify these algorithms, which show that LU-SGS algorithm introduces errors on boundary cells. When partition boundaries are circumferential, errors arise in proportion to grid speed, accumulating along with the rotation, and leading to computational failure in the end. Meanwhile, DP-LUR and HLU-SGS methods show good convergence owing to boundary treatment which are desirable in domain decomposition parallel computations. [ABSTRACT FROM AUTHOR]

Computational Fluid Dynamics (CFD) is an important branch of fluid mechanics, and will continue to play great roles on the design of aerospace vehicles, exploration of new concept vehicles and new aerodynamic technology. This paper will present the progress of CFD from point of view of engineering application in recent years at CARDC, including the software integration, grid technique, speeding up of convergence, unsteady fluid computation-etc., and also give some engineering application examples of CFD at CARDC. [ABSTRACT FROM AUTHOR]