摘要
民机的高速抖振通常是由机翼上激波诱导的分离所致,而发动机动力效应可能会对机翼上激波的强度带来明显影响。基于经过TPS标模及DLR-F6标模算例验证的、在多块结构化网格系统上求解雷诺平均NS方程的数值方法,结合通过定常计算结果判定抖振发生原因及起始升力系数的方法,研究发动机动力效应对某民机巡航构型高速抖振特性的影响。结果表明:动力效应给基于通气短舱设计外形的高速抖振特性带来了不利影响,使其抖振起始升力系数降低约1.3%总升力系数。
The high speed buffet of the civil aircraft usually results from separation induced by the shock wave that is on the wing, but the strength of shock wave on the wing could obviously be affected by powered effects of engine. The research is done about the interference of the powered effects to high speed buffet characteristics on the cruise configuration of a civil aircraft with method of solving RANS equations on multi-block structured grid system. Firstly, it is verified that the powered effects can be modeled by intake and exhaust boundary condi- tions. Secondly, the method that it can be used to judge buffeting onset is given by comprehensive consideration of calculation accuracy and efficiency in the preliminary design stage. Analysis shows： the powered effects has a bad interference to buffeting onset that is designed based on flow-through nacelle at the cruise Math number, lift coefficient of buffeting onset is reduced about 1.3% of total
出处
《航空工程进展》
CSCD
2016年第3期301-308,共8页
Advances in Aeronautical Science and Engineering
关键词
数值模拟
通气短舱
动力短舱
进排气边界
抖振特性
numerical simulation
flow-through nacelle
powered nacelle
intake and exhaust boundary condi-tions
buffet characteristics
