CAJ | 학술논문

在飞机设计阶段，获得准确的气动特性数据对设计者是十分重要的，采用缩比模型的风洞试验是主要途径之一。但是风洞条件限制了试验的Re数，从而影响了对跨音速巡航阻力的评估，因此需要对风洞试验结果的阻力进行Re数效应修正。分析了风洞试验结果阻力的误差构成，提出了Re数效应修正的风洞试验数据基础；进一步就跨音速巡航阻力的构成进行分析，论述了对最小阻力和升致阻力分项修正的方法，并对修正结果进行了验证，得到了一种可靠的工程方法。
재비궤설계계단，획득준학적기동특성수거대설계자시십분중요적，채용축비모형적풍동시험시주요도경지일。단시풍동조건한제료시험적Re수，종이영향료대과음속순항조력적평고，인차수요대풍동시험결과적조력진행Re수효응수정。분석료풍동시험결과조력적오차구성，제출료Re수효응수정적풍동시험수거기출；진일보취과음속순항조력적구성진행분석，논술료대최소조력화승치조력분항수정적방법，병대수정결과진행료험증，득도료일충가고적공정방법。
It is important to get the accuracy aerodynamic character data for designers during the airplane design phase. The wind tunnel test with scaled model is one of the main ways. The wind tunnel’ s finite Re number limit the assessment of the transonic cruise drag, so we have to make the Re number effect correction for the drag of wind tunnel test. This article analyses the tolerance of wind tunnel drag measurement, and presents the wind tunnel test data basis for Re number effect correction. The constitution of transonic cruise drag is analyzed . The correct meth-od of the Min-Drag and Lift-Induced-Drag is discussed respectively, and the result is verified to get a reliable en-gineering method.