【摘要】 瞄准民用航空发动机的动力短舱的推阻分解问题,应用基于计算流体力学的方法进行推力与阻力的计算。首先对动力短舱进行控制体受力分析,明确各项气动力的计算方法,然后采用三个验证算例对推阻分解方法进行应用验证:NACA 1-85-75进气道算例表明,该方法能够很好地计算进气道的溢流阻力,计算结果与试验符合较好;DSFR双涵道喷管算例显示该方法对喷管速度系数的计算误差大约为0.003~0.004左右,有良好的预测效果;最后采用NAL-AERO-02-01TPS短舱算例演示和验证推阻分解过程,并应用该方法排除了喷管阻力的影响,分析了短舱外阻随马赫数的变化趋势。更多还原

【Abstract】 This paper focuses on the thrust and drag determination of the powered-on nacelle of civil airplanes.The thrust-drag bookkeeping method based on computational fluid dynamics is used to compute the thrust and drag.First,the control volume analysis of a powered-on nacelle is applied to study the computation methods for each force component.Then three test cases are numerically investigated to demonstrate the thrust-drag bookkeeping process and accuracy.The NACA 1-85-75 inlet test case shows that the present method has reasonable accuracy on the inlet spillage drag.The computation results agree well with the experimental data.The DSFR nozzle from the propulsion aerodynamics workshop 2 is used to test the prediction precision on nozzle performance.The results show that the present computation method is well validated.The deviation between the computation result and experimental data is 0.003 to 0.004.The NAL-AERO-02-01 TPS nacelle case is adopted to demonstrate the process of the thrust-drag bookkeeping process.With the bookkeeping method,the nacelle drag variation with Mach number is revealed and associated with the flow phenomena on the nacelle.更多还原