摘要
针对超音速和高超音速流动的特点 ,分析并检验了各种气动力工程算法 (牛顿法 ,切楔 /切锥法 ,活塞理论 ,激波膨胀波法等 ) ,并将其推广运用于超音速和高超音速机翼的非定常气动力的计算中。通过与机翼结构运动方程的联立求解 ,在时间域内实现了超音速和高超音速机翼颤振的数值模拟。通过与实验结果的比较 ,证明该方法具有较高精度 ,误差能控制在 1 0 %左右。
Existing engineering methods for computing aeroelastic characteristics of supersonic wing, in our opinion, can only deal with thin supersonic wing with sharp leading edge. We combine existing engineering methods in such a way as to make computing aeroelastic characteristics possible for both thin and thick wings and for both sharp and blunt leading edges. Section 1 first presents briefly various methods for computing aerodynamic loads (Newtonian theory, piston theory, tangent wedge/tangent cone method, shock wave and expansion wave method) according to the characteristics of supersonic or hypersonic flow. Then section 1 combines these methods to solve for the pressure distribution on an arbitrarily shaped body and extends the combined method to solve for the unsteady pressure distribution in supersonic or hypersonic flow. Section 2 solves the governing structural equations of the system in the time domain by numerical method. We like to point out that time domain method can deal with the non linearity of hypersonic aeroelasticity. Section 3 gives numerical simulation results. Fig.3 gives computed results for a specific supersonic wing and Table 2 shows that calculated flutter speeds are within 10% of experimentally determined ones. Fig.4 gives computed results for a specific hypersonic wing. For hypersonic wing, we have found some non linear phenomena such as LCO (limit cycle oscillation). Fig.5(a) shows variations of flutter speed with increasing Mach number for four different angles of attack. Fig.5(b) shows variations of flutter speed with increasing angle of attack for seven different Mach numbers.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2003年第6期687-691,共5页
Journal of Northwestern Polytechnical University
基金
"8 6 3"国家高技术研究发展计划 ( 2 0 0 3AA72 5 0 4 1)
关键词
超音速
高超音速
颤振
气动弹性
supersonic wing, hypersonic wing, flutter, non linearity, aeroelasticity
