翼端終板於全尺寸地效飛行器之數值研究

Numerical Studies of the Effect of Endplates on a Full-scaled WIG Configuration

戴昌賢(Chang-Hsien Tai) ； 徐子圭(Uzu-Kuei Hsu) ； 苗志銘(Jr-Ming Miao) ； 吳振源(Chen-Yuan Wu)

《中國航空太空學會學刊》 36卷4期 (2004/12) Pp. 359-366

https://doi.org/10.6124/TAASRC.200412_36(4).05

摘要

由於真實三維地效飛行器流場中包含了可壓縮流與不可壓縮流相互夾雜，故本研究主要研改預調式Navier-Stokes方程式成爲可適性預調法爲自行開發之程式HASP，使能應用於結構化網格之三維多區塊複雜具可壓縮流與不可壓縮流地效飛行器流場，程式中採用有限體積法對統御方程式進行離散，爲能獲得較精確之流場性質採用多步階、上風通量差分等數值法則，同時結合AUSM之低耗散程式，用以模擬氣流流經具終板地效飛行器之流場現象。研究結果顯示：終板對地效飛行器造成上翼面流場會產生不穩定現象，但對整體升力之提升可增加約25%。

關鍵字

可適性預調法 ； 終板 ； 地效飛行器 ； 有限體積法

並列摘要

For real 3D WIG flying, the flowfield consist of compressible and incompressible flow. In this study, a density-based solver HASP, developed by the authors, for the solution of the preconditioned Reynolds-averaged Navier-Stokes (RANS) equations on multiblock structured meshes is presented to simulate the complex flow field in a WIG. The RANS equations are preconditioned by the time-derivative preconditioning to permit solution of both compressible and incompressible flows. In the space discretization, a cell-centered, finite-volume method is used in conjunction with AUSMDV, a minmod limiter and a van Leer κ scheme in the MUSCL variable extrapolation frame to increase a second-order accuracy. The time-integration scheme employs a two-stage Runge-Kutta method combined with the Hancock method and implicit residual smoothing to accelerate convergence rates. According to the results of this research, this analyzer can indeed effectively modulate and simulate the aerodynamic characteristic of the WIG. The Endplate affects the flow unstable upper the wing, but the WIG lift increases 25%.

並列關鍵字

Preconditioning ； Endplate ； WIG ； Finite volume