针对某车型高速行驶时外后视镜附近气动噪声较大的问题,基于格子波尔兹曼理论和统计能量分析法进行整车气动噪声模拟计算,得到气动噪声初始状态模拟计算曲线,通过进一步模拟计算发现,改进外后视镜挡水条可有效降低该车气动噪声,同时对...针对某车型高速行驶时外后视镜附近气动噪声较大的问题,基于格子波尔兹曼理论和统计能量分析法进行整车气动噪声模拟计算,得到气动噪声初始状态模拟计算曲线,通过进一步模拟计算发现,改进外后视镜挡水条可有效降低该车气动噪声,同时对改进后的外后视镜进行风洞测试,测试结果表明:改进后的挡水条可有效降低整车气动噪声,特别是在4 000 Hz处,可降低约5 d B。外后视镜挡水条对整车气动噪声影响很大,在今后外后视镜的设计开发中,为了减少挡水条造型对气动噪声的影响,应尽量避免将挡水条设计在外后视镜镜脚处。展开更多
The efficiency of the aircraft Ice Protection Systems(IPSs)needs to be verified through icing wind tunnel tests.However,the scaling method for testing the IPSs has not been systematically established yet,and further r...The efficiency of the aircraft Ice Protection Systems(IPSs)needs to be verified through icing wind tunnel tests.However,the scaling method for testing the IPSs has not been systematically established yet,and further research is needed.In the present study,a scaling method specifically designed for thermal IPSs was derived from the governing equation of thin water film.Five scaling parameters were adopted to address the heat and mass transfer involved in the thermal anti-icing process.For method validation,icing wind tunnel tests were conducted using a jet engine nacelle model equipped with a bleed air IPS.The non-dimensional surface temperature and runback ice closely matched for both the reference and scaled conditions.The validation confirms that the scaling method is capable of achieving the similarity of surface temperature and the runback ice coverage.The anti-icing scaling method can serve as an important supplement to the existing icing similarity theory.展开更多
文摘针对某车型高速行驶时外后视镜附近气动噪声较大的问题,基于格子波尔兹曼理论和统计能量分析法进行整车气动噪声模拟计算,得到气动噪声初始状态模拟计算曲线,通过进一步模拟计算发现,改进外后视镜挡水条可有效降低该车气动噪声,同时对改进后的外后视镜进行风洞测试,测试结果表明:改进后的挡水条可有效降低整车气动噪声,特别是在4 000 Hz处,可降低约5 d B。外后视镜挡水条对整车气动噪声影响很大,在今后外后视镜的设计开发中,为了减少挡水条造型对气动噪声的影响,应尽量避免将挡水条设计在外后视镜镜脚处。
基金supported by the National Major Science and Technology Projects of China(J2019-Ⅲ-0010-0054).
文摘The efficiency of the aircraft Ice Protection Systems(IPSs)needs to be verified through icing wind tunnel tests.However,the scaling method for testing the IPSs has not been systematically established yet,and further research is needed.In the present study,a scaling method specifically designed for thermal IPSs was derived from the governing equation of thin water film.Five scaling parameters were adopted to address the heat and mass transfer involved in the thermal anti-icing process.For method validation,icing wind tunnel tests were conducted using a jet engine nacelle model equipped with a bleed air IPS.The non-dimensional surface temperature and runback ice closely matched for both the reference and scaled conditions.The validation confirms that the scaling method is capable of achieving the similarity of surface temperature and the runback ice coverage.The anti-icing scaling method can serve as an important supplement to the existing icing similarity theory.
