CAJ | 학술논문

基于自动微分原理和 NS 方程有限体积方法建立了一套翼型敏感性导数计算方法和程序，可以一次性获得翼型不同气动力系数、压力分布对模型几何外形误差的敏感性导数和不确定度。计算结果表明，在跨声速范围内，即使翼型的外形误差只有63μm（弦长1m），也可以给翼型压力分布带来0．312（以来流动压为参考）量级的不确定度，而激波处的流动最为敏感。这种自动微分方法对于分析数值模拟结果的分散性、风洞试验结果的分散性或不确定性具有很好的指导意义。
기우자동미분원리화 NS 방정유한체적방법건립료일투익형민감성도수계산방법화정서，가이일차성획득익형불동기동력계수、압력분포대모형궤하외형오차적민감성도수화불학정도。계산결과표명，재과성속범위내，즉사익형적외형오차지유63μm（현장1m），야가이급익형압력분포대래0．312（이래류동압위삼고）량급적불학정도，이격파처적류동최위민감。저충자동미분방법대우분석수치모의결과적분산성、풍동시험결과적분산성혹불학정성구유흔호적지도의의。
Focused on the quantification of the uncertainties of areodynamics performance of airfoils with respect to geometry error,with a set of CFD program based on finite volume algorithm solving the Reynolds-Averaged Navier-Stokes equations with S-A turbulent model,adopting automatic differentiation method to reform the program simultaniously,all kinds of sensitive derivatives,uncertainties of all kinds of aerody-namic coefficients and pressure coefficients distribution resulting from geometry error could be obtained in one course of computation.As the computational results show,even if the geometry error is only 63 microns (while the length of chord is 1 meter),the pressure distribution of the walls could be influenced obviously with uncertainty quantity reaching 0.312 (taking dynamic pressure of the flow as reference)for an airfois in transonic flow,moreover,pressure attached to the place where shock wave stationed bears peak uncertainty. the results of method of automatic differentiation account for the dispersity of results of numeric simulations and wind tunnel experiments well.