The development of the Urban Air Mobility concept has proposed stringent requirements for the fixed-wing vehicle’s Short/Vertical Take-Off and Landing(S/VTOL)performance.With its lift-enhancing impact,the channel win...The development of the Urban Air Mobility concept has proposed stringent requirements for the fixed-wing vehicle’s Short/Vertical Take-Off and Landing(S/VTOL)performance.With its lift-enhancing impact,the channel wing,can improve aircraft low-speed performance and Short Take-Off and Landing(STOL)capability.It is critical for the performance analysis and flow mechanism study of a channel wing that considers the influence of propeller slipstream to guide the design of S/VTOL aircraft.The law and mechanism for the effect of the enclosing angle of the arc wing,the phase angle of the propeller,the tip clearance,the rotational speed and the chordwise position of the propeller on the channel wing are explored utilizing the quasi-steady multi reference frame method.A channel wing with a larger enclosing angle has a better ability to enhance lift and reduce drag using propeller slipstream.The effect of propeller phase angle on channel wing aerodynamic forces is periodic and weak.Increasing propeller rotational speed is helpful to enhance lift and resist flow separation for channel wing.It can reduce drag for tractor configuration but increase drag for pusher configuration.However,the nose-down pitching moment of a channel wing will grow dramatically,making longitudinal trimming in aircraft layout design challenging.展开更多
In this work,the flow surrounding the train was obtained using a detached eddy simulation(DES)for slipstream analysis.Two different streamlined nose lengths were investigated:a short nose(4 m)and a long nose(9 m).The ...In this work,the flow surrounding the train was obtained using a detached eddy simulation(DES)for slipstream analysis.Two different streamlined nose lengths were investigated:a short nose(4 m)and a long nose(9 m).The time-average slipstream velocity and the time-average slipstream pressure along the car bodies were compared and explained in detail.In addition to the time-averaged values,the _(max)imum velocities and the pressure peak-to-peak values around the two trains were analyzed.The result showed that the nose length affected the slipstream velocity along the entire train length at the lower and upper regions of the side of the train.However,no significant effect was recognized at the middle height of the train along its length,except in the nose region.Moreover,within the train’s side regions(y=2.0-2.5 m and z=2-4 m)and(y=2.5-3.5 m and z=0.2-0.7 m),the ratio of slipstream velocity U_(max) between the short and long nose trains was notably higher.This occurrence also manifested at the train’s upper section,specifically where y=0-2.5 m and z=4.2-5.0 m.Similarly,regarding the ratio of _(max)imum pressure peak-to-peak values Cp-p_(max),significant regions were observed at the train’s side(y=1.8-2.6 m and z=1-4 m)and above the train(y=0-2 m and z=3.9-4.8 m).展开更多
The efficient utilization of propeller slipstream energy is important for improving the ultra-short takeoff and landing capability of Distributed Electric Propulsion(DEP)aircraft.This paper presents a quasi-three-dime...The efficient utilization of propeller slipstream energy is important for improving the ultra-short takeoff and landing capability of Distributed Electric Propulsion(DEP)aircraft.This paper presents a quasi-three-dimensional(2.5D)high-lift wing design approach considering the three-dimensional(3D)effects of slipstream for DEP aircraft,aiming at maximizing the comprehensive lift enhancement benefit of the airframe-propulsion coupling unit.A high-precision and efficient momentum source method is adopted to simulate the slipstream effects,and the distributed propellers are replaced by a rectangular actuator disk to reduce the difficulty of grid generation and improve the grid quality.A detailed comparison of the 2.5D and 3D configurations based on the X-57 ModⅣis performed in terms of flow characteristics and computational cost to demonstrate the rationality of the above design approach.The optimization results of the high-lift wing of the X-57 ModⅣshow that the aerodynamic performance of the landing configuration is significantly improved,for instance,the lift coefficient increases by 0.094 at the angle of attack of 7°,and 0.097 at the angle of attack of 14°.This novel approach achieves efficient and effective design of high-lift wings under the influence of distributed slipstream,which has the potential to improve the design level of DEP aircraft.展开更多
The cave is of great importance for the storage of equipment and to avoid having workers in the tunnel,but it changes the tunnel section,leads to a change of slipstream and affects the safety of trains and workers.The...The cave is of great importance for the storage of equipment and to avoid having workers in the tunnel,but it changes the tunnel section,leads to a change of slipstream and affects the safety of trains and workers.The Re-normalization group(RNG)k-εturbulence method is used to investigate the slipstream induced by a single train passing through a double-track tunnel at 350 km/h.The slipstream in a tunnel with and without a cave is compared.The slipstream components in three directions are reported comprehensively.The results show that the existence of a cave changes the slipstream at the tail of the train.At measurement points before and after the train passes the cave,the intensity of the slipstream at the tail ismitigated;as the train passes the cave,the tail slipstream is enhanced to a certain extent.With increasing lateral distance,the peak value of the slipstream with a cave decreases faster than that without a cave.These findings suggest that the presence of a cave mitigates the slipstream intensity,but special attention should be paid to the design of ancillary facilities,especially their relative location.展开更多
为了快速、准确分析螺旋桨滑流对增升装置的影响,采用实桨非定常方法(full blades method,FBM)和定常动量激励盘方法(actuator disk method,ADM),数值计算分析了前进比J=0.7、1.0,攻角α=–4°~24°工况下螺旋桨滑流对高升力构...为了快速、准确分析螺旋桨滑流对增升装置的影响,采用实桨非定常方法(full blades method,FBM)和定常动量激励盘方法(actuator disk method,ADM),数值计算分析了前进比J=0.7、1.0,攻角α=–4°~24°工况下螺旋桨滑流对高升力构型的影响。研究表明:虽然从单独螺旋桨获取的时均化激励盘载荷分布与从高升力构型螺旋桨获取的存在局部差异,但将来源不同的激励盘载荷应用于ADM计算时,所得高升力构型的压力分布、升阻力结果基本一致,全机升力系数差异不超过4.3%,阻力系数偏差小于5.4%,说明采用单独螺旋桨获取激励盘载荷对全机气动力计算影响不大,从而避免了复杂的网格生成。ADM将非定常计算转化为定常计算,在保持网格量相当(3300万)的条件下,其计算结果与FBM结果在失速前(α<20°时)基本吻合,同时计算核时约降低至FBM的1/18(170/3100)。因此ADM方法能够高效、合理评估出螺旋桨滑流对增升装置产生的影响。展开更多
基金supported by the Fundamental Research Funds for the Central Universities,China(No.D5000220505)the Central Funds Guiding the Local Science and Technology Development,China(No.2021Szvup1).
文摘The development of the Urban Air Mobility concept has proposed stringent requirements for the fixed-wing vehicle’s Short/Vertical Take-Off and Landing(S/VTOL)performance.With its lift-enhancing impact,the channel wing,can improve aircraft low-speed performance and Short Take-Off and Landing(STOL)capability.It is critical for the performance analysis and flow mechanism study of a channel wing that considers the influence of propeller slipstream to guide the design of S/VTOL aircraft.The law and mechanism for the effect of the enclosing angle of the arc wing,the phase angle of the propeller,the tip clearance,the rotational speed and the chordwise position of the propeller on the channel wing are explored utilizing the quasi-steady multi reference frame method.A channel wing with a larger enclosing angle has a better ability to enhance lift and reduce drag using propeller slipstream.The effect of propeller phase angle on channel wing aerodynamic forces is periodic and weak.Increasing propeller rotational speed is helpful to enhance lift and resist flow separation for channel wing.It can reduce drag for tractor configuration but increase drag for pusher configuration.However,the nose-down pitching moment of a channel wing will grow dramatically,making longitudinal trimming in aircraft layout design challenging.
基金Project(52202426)supported by the National Natural Science Foundation of ChinaProjects(15205723,15226424)supported by the Research Grants Council of the Hong Kong Special Administrative Region(SAR),China+1 种基金Project(K2021J041)supported by the Technology Research and Development Program of China RailwayProject(1-BD23)supported by The Hong Kong Polytechnic University,China。
文摘In this work,the flow surrounding the train was obtained using a detached eddy simulation(DES)for slipstream analysis.Two different streamlined nose lengths were investigated:a short nose(4 m)and a long nose(9 m).The time-average slipstream velocity and the time-average slipstream pressure along the car bodies were compared and explained in detail.In addition to the time-averaged values,the _(max)imum velocities and the pressure peak-to-peak values around the two trains were analyzed.The result showed that the nose length affected the slipstream velocity along the entire train length at the lower and upper regions of the side of the train.However,no significant effect was recognized at the middle height of the train along its length,except in the nose region.Moreover,within the train’s side regions(y=2.0-2.5 m and z=2-4 m)and(y=2.5-3.5 m and z=0.2-0.7 m),the ratio of slipstream velocity U_(max) between the short and long nose trains was notably higher.This occurrence also manifested at the train’s upper section,specifically where y=0-2.5 m and z=4.2-5.0 m.Similarly,regarding the ratio of _(max)imum pressure peak-to-peak values Cp-p_(max),significant regions were observed at the train’s side(y=1.8-2.6 m and z=1-4 m)and above the train(y=0-2 m and z=3.9-4.8 m).
文摘The efficient utilization of propeller slipstream energy is important for improving the ultra-short takeoff and landing capability of Distributed Electric Propulsion(DEP)aircraft.This paper presents a quasi-three-dimensional(2.5D)high-lift wing design approach considering the three-dimensional(3D)effects of slipstream for DEP aircraft,aiming at maximizing the comprehensive lift enhancement benefit of the airframe-propulsion coupling unit.A high-precision and efficient momentum source method is adopted to simulate the slipstream effects,and the distributed propellers are replaced by a rectangular actuator disk to reduce the difficulty of grid generation and improve the grid quality.A detailed comparison of the 2.5D and 3D configurations based on the X-57 ModⅣis performed in terms of flow characteristics and computational cost to demonstrate the rationality of the above design approach.The optimization results of the high-lift wing of the X-57 ModⅣshow that the aerodynamic performance of the landing configuration is significantly improved,for instance,the lift coefficient increases by 0.094 at the angle of attack of 7°,and 0.097 at the angle of attack of 14°.This novel approach achieves efficient and effective design of high-lift wings under the influence of distributed slipstream,which has the potential to improve the design level of DEP aircraft.
基金the High-Speed Train Research Center of Central South University,China.Thiswork was supported by the National Key Research and Development Program of China(Grant No.2020YFA0710903-01)the Graduate Student Independent Innovation Project of Hunan Province(Grant No.CX20200196).
文摘The cave is of great importance for the storage of equipment and to avoid having workers in the tunnel,but it changes the tunnel section,leads to a change of slipstream and affects the safety of trains and workers.The Re-normalization group(RNG)k-εturbulence method is used to investigate the slipstream induced by a single train passing through a double-track tunnel at 350 km/h.The slipstream in a tunnel with and without a cave is compared.The slipstream components in three directions are reported comprehensively.The results show that the existence of a cave changes the slipstream at the tail of the train.At measurement points before and after the train passes the cave,the intensity of the slipstream at the tail ismitigated;as the train passes the cave,the tail slipstream is enhanced to a certain extent.With increasing lateral distance,the peak value of the slipstream with a cave decreases faster than that without a cave.These findings suggest that the presence of a cave mitigates the slipstream intensity,but special attention should be paid to the design of ancillary facilities,especially their relative location.
文摘为了快速、准确分析螺旋桨滑流对增升装置的影响,采用实桨非定常方法(full blades method,FBM)和定常动量激励盘方法(actuator disk method,ADM),数值计算分析了前进比J=0.7、1.0,攻角α=–4°~24°工况下螺旋桨滑流对高升力构型的影响。研究表明:虽然从单独螺旋桨获取的时均化激励盘载荷分布与从高升力构型螺旋桨获取的存在局部差异,但将来源不同的激励盘载荷应用于ADM计算时,所得高升力构型的压力分布、升阻力结果基本一致,全机升力系数差异不超过4.3%,阻力系数偏差小于5.4%,说明采用单独螺旋桨获取激励盘载荷对全机气动力计算影响不大,从而避免了复杂的网格生成。ADM将非定常计算转化为定常计算,在保持网格量相当(3300万)的条件下,其计算结果与FBM结果在失速前(α<20°时)基本吻合,同时计算核时约降低至FBM的1/18(170/3100)。因此ADM方法能够高效、合理评估出螺旋桨滑流对增升装置产生的影响。
