可变形翼型的非定常气动特性研究
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摘要
可变形飞行器是为了满足航天航空技术飞速发展的需求而提出来的一种新概念且能够适应多环境,执行多任务的飞行器。与传统的固定外形飞行器相比,可变形飞行器能够根据飞行环境和作战任务等需求自适应改变外形,使其在整个飞行过程中和执行任务时,始终保持全阶段的性能最优化。可变性飞行技术被广泛认为是实现未来航天航空飞行器新突破的革命性技术之一
由于可变形飞行器的优越性使其成为近年来研究者关注的焦点之一,其中可变形飞行器的气动布局和气动特性是可变形飞行器研究的基本出发点和核心。可变形飞行器的研究作为一个崭新的研究领域,各国的研究情况还处于不同程度的起步阶段,其中许多基础性的科学问题和关键性技术的研究还相对薄弱。因此本文的工作是针对如何改变翼型以适应不同飞行条件要求这一复杂问题来开展研究的。
本文以儒可夫斯基翼型为例,采用理论分析和数值计算相结合的方法研究二维可变形机翼的非定常气动特性,具体研究内容如下：
1、为了从理论上认识和分析可变形机翼非定常气动性能,本文对于不可压理想流体来流条件下,利用复变函数论,理论推导了可变形儒可夫斯基翼型的非定常气动升力和阻力的解析公式,同时也为后续关于可变形机翼数值计算的验证提供了检验方法。
2、对于不可压缩理想流体来流条件下,提出了利用解析解和离散涡的相结合的方法研究可变形儒可夫斯基翼型的流场及非定常气动力,较详细地分析了变形机翼升力系数的准定常计算方法的误差来源,并给出了修正方案。计算结果显示脱落涡尾迹对升力系数和绕流环量影响很小,变形机翼升力系数准定常计算方法的误差主要来源于流体非定常运动引起的附加升力,该非定常附加升力系数仅与当前时刻飞行姿态及翼型形状和变形速率有关,与具体的变形历史过程无关,变形机翼的升力系数近似等于准定常计算结果叠加上相应的非定常附加升力系数。
3、在亚音速流动条件下,利用仿射变换将可压缩流动转化为不可压缩流动的速度场,利用不压缩流动计算方法计算流动速度场,再利用逆变换转化为相应的亚音速流动的速度场,进而分析了机翼变形的非定常气动特性。建立了变形机翼准定常升力系数和非定常附加升力系数在可压缩和不可压缩两种状态下的简单近似对应关系；着重分析了机翼往复变形过程中升力变化特性。
4、在超音速流动条件下,从小扰动线化方程出发,利用基于格林函数的边界元法求解了二维超音速流动速度场,进而对变形机翼的气动特性进行理论分析和数值计算。重点讨论了非定常附加升力系数随着翼型基本参数变化的关系；同时还给出了不同来流马赫数、攻角以及翼型参数变形加速度对完成机翼往复变形时的气动特性所造成影响。
综上所述,本文的工作是针对理想流体在低速、亚音速以及超音速来流条件下,利用理论分析和数值模拟相结合的方法,研究了二维可变形儒可夫斯基翼型的非定常气动特性。希望本文所研究的工作能给工程实践带来帮助。
Morphing aircraft is a bran-new concept proposed to meet the needs of the rapid development of aerospace technology, which is able to adapt to multi-environment and perform multi-mission. Compared with the traditional aircraft with fixed-shape, morphing aircraft can self-adaptive morph according to flight circumstance and battle mission to maintain an all-stage optimal performance throughout the flight and mission. The morphing flight technology is widely regarded as one of the potentially revolutionary technology to realize the new breakthrough of the future aviation aircraft.
The advantage of morphing aircraft makes it become a research hotspot in recent years. Aerodynamic characteristic is the fundamental for the research of morphing aircraft. As a bran-new research field, its scientific fundamentals and key technology for morphing aircraft are still in beginning stage. In this thesis, how to change the airfoil shape to adapt the different flight conditions is studied.
The studies are carried out based on the morphing Joukowski airfoil, using the theoretical analysis and numerical simulations to study the unsteady aerodynamic characteristics for2D-morphing airfoils. The works can be summarized as follows:
1. As an initial study on the theoretically investigating the unsteady aerodynamic characteristics for morphing airfoil, under the inviscid incompressible ideal fluid flow conditions, we derive the unsteady aerodynamic lift and resistance formula for the morphing Joukowski airfoil by using complex function theory. These analytical results can be used to test the program code for numerical simulations of morphing airfoil.
2. Under the inviscid incompressible ideal fluid flow conditions, the unsteady flow field and aerodynamic lift for the morphing Joukowski airfoil are calculated by combining the analytical solution and the discrete vortex method together. The error sources of the quasi-steady assumption are analyzed rigorously and correspondingly the error correction method is proposed. Numerical calculations show that the vortex wake of morphing airfoil has almost no effect on the lift coefficient and the circulation around the airfoil. The additional unsteady aerodynamic lift caused by unsteady fluid flow due to the airfoil deformation is the main error source of the quasi-steady solution for the aerodynamic lift of morphing airfoil. It is also shown that the temporal flight attitude, the airfoil profiles and the deformation velocity determine the unsteady additional lift coefficient, which has little relation with the evolutionary history of deformation. It is proposed that the lift coefficient of morphing airfoil is approximately equal to the lift coefficient of the quasi-steady assumption solution adding the corresponding additional unsteady lift coefficient.
3. The subsonic flow for the morphing Joukowski airfoil is transformed into incompressible flow by using an affine transformation. Then the subsonic flow can be calculated with the inverse affine transformation from the corresponding incompressible flow problem, which is solved by combining the analytical solution and the discrete vortex method together. In this chapter, for the quasi-steady aerodynamic force and the additional unsteady aerodynamic lift caused by the virtual mass force, the simple relationships between the subsonic flow and the corresponding incompressible flow are proposed. The aerodynamic characteristics of the morphing airfoil during reciprocating deformation are investigated.
4. The two-dimensional small-perturbation equations governing the supersonic flow-past the morphing airfoils are calculated using the boundary element method based upon the Green formula. The unsteady supersonic aerodynamic characteristics for morphing airfoil are studied analytically and numerically. The relationships for the unsteady lift coefficient as a function of the geometry parameters for the morphing airfoil are discussed. The influences of different free-stream Mach, the angle of attack and morphing acceleration on aerodynamic characteristics during the reciprocating deformation are obtained.
In summary, the study for unsteady aerodynamic characteristics of two-dimensional morphing Joukowski airfoil by theoretical analysis and numerical calculation is performed under the incompressible, subsonic and supersonic flow conditions for inviscid fluid. The research of this work is expected to have a practical help to the engineering practice in the future.
由于可变形飞行器的优越性使其成为近年来研究者关注的焦点之一,其中可变形飞行器的气动布局和气动特性是可变形飞行器研究的基本出发点和核心。可变形飞行器的研究作为一个崭新的研究领域,各国的研究情况还处于不同程度的起步阶段,其中许多基础性的科学问题和关键性技术的研究还相对薄弱。因此本文的工作是针对如何改变翼型以适应不同飞行条件要求这一复杂问题来开展研究的。
本文以儒可夫斯基翼型为例,采用理论分析和数值计算相结合的方法研究二维可变形机翼的非定常气动特性,具体研究内容如下：
1、为了从理论上认识和分析可变形机翼非定常气动性能,本文对于不可压理想流体来流条件下,利用复变函数论,理论推导了可变形儒可夫斯基翼型的非定常气动升力和阻力的解析公式,同时也为后续关于可变形机翼数值计算的验证提供了检验方法。
2、对于不可压缩理想流体来流条件下,提出了利用解析解和离散涡的相结合的方法研究可变形儒可夫斯基翼型的流场及非定常气动力,较详细地分析了变形机翼升力系数的准定常计算方法的误差来源,并给出了修正方案。计算结果显示脱落涡尾迹对升力系数和绕流环量影响很小,变形机翼升力系数准定常计算方法的误差主要来源于流体非定常运动引起的附加升力,该非定常附加升力系数仅与当前时刻飞行姿态及翼型形状和变形速率有关,与具体的变形历史过程无关,变形机翼的升力系数近似等于准定常计算结果叠加上相应的非定常附加升力系数。
3、在亚音速流动条件下,利用仿射变换将可压缩流动转化为不可压缩流动的速度场,利用不压缩流动计算方法计算流动速度场,再利用逆变换转化为相应的亚音速流动的速度场,进而分析了机翼变形的非定常气动特性。建立了变形机翼准定常升力系数和非定常附加升力系数在可压缩和不可压缩两种状态下的简单近似对应关系；着重分析了机翼往复变形过程中升力变化特性。
4、在超音速流动条件下,从小扰动线化方程出发,利用基于格林函数的边界元法求解了二维超音速流动速度场,进而对变形机翼的气动特性进行理论分析和数值计算。重点讨论了非定常附加升力系数随着翼型基本参数变化的关系；同时还给出了不同来流马赫数、攻角以及翼型参数变形加速度对完成机翼往复变形时的气动特性所造成影响。
综上所述,本文的工作是针对理想流体在低速、亚音速以及超音速来流条件下,利用理论分析和数值模拟相结合的方法,研究了二维可变形儒可夫斯基翼型的非定常气动特性。希望本文所研究的工作能给工程实践带来帮助。
Morphing aircraft is a bran-new concept proposed to meet the needs of the rapid development of aerospace technology, which is able to adapt to multi-environment and perform multi-mission. Compared with the traditional aircraft with fixed-shape, morphing aircraft can self-adaptive morph according to flight circumstance and battle mission to maintain an all-stage optimal performance throughout the flight and mission. The morphing flight technology is widely regarded as one of the potentially revolutionary technology to realize the new breakthrough of the future aviation aircraft.
The advantage of morphing aircraft makes it become a research hotspot in recent years. Aerodynamic characteristic is the fundamental for the research of morphing aircraft. As a bran-new research field, its scientific fundamentals and key technology for morphing aircraft are still in beginning stage. In this thesis, how to change the airfoil shape to adapt the different flight conditions is studied.
The studies are carried out based on the morphing Joukowski airfoil, using the theoretical analysis and numerical simulations to study the unsteady aerodynamic characteristics for2D-morphing airfoils. The works can be summarized as follows:
1. As an initial study on the theoretically investigating the unsteady aerodynamic characteristics for morphing airfoil, under the inviscid incompressible ideal fluid flow conditions, we derive the unsteady aerodynamic lift and resistance formula for the morphing Joukowski airfoil by using complex function theory. These analytical results can be used to test the program code for numerical simulations of morphing airfoil.
2. Under the inviscid incompressible ideal fluid flow conditions, the unsteady flow field and aerodynamic lift for the morphing Joukowski airfoil are calculated by combining the analytical solution and the discrete vortex method together. The error sources of the quasi-steady assumption are analyzed rigorously and correspondingly the error correction method is proposed. Numerical calculations show that the vortex wake of morphing airfoil has almost no effect on the lift coefficient and the circulation around the airfoil. The additional unsteady aerodynamic lift caused by unsteady fluid flow due to the airfoil deformation is the main error source of the quasi-steady solution for the aerodynamic lift of morphing airfoil. It is also shown that the temporal flight attitude, the airfoil profiles and the deformation velocity determine the unsteady additional lift coefficient, which has little relation with the evolutionary history of deformation. It is proposed that the lift coefficient of morphing airfoil is approximately equal to the lift coefficient of the quasi-steady assumption solution adding the corresponding additional unsteady lift coefficient.
3. The subsonic flow for the morphing Joukowski airfoil is transformed into incompressible flow by using an affine transformation. Then the subsonic flow can be calculated with the inverse affine transformation from the corresponding incompressible flow problem, which is solved by combining the analytical solution and the discrete vortex method together. In this chapter, for the quasi-steady aerodynamic force and the additional unsteady aerodynamic lift caused by the virtual mass force, the simple relationships between the subsonic flow and the corresponding incompressible flow are proposed. The aerodynamic characteristics of the morphing airfoil during reciprocating deformation are investigated.
4. The two-dimensional small-perturbation equations governing the supersonic flow-past the morphing airfoils are calculated using the boundary element method based upon the Green formula. The unsteady supersonic aerodynamic characteristics for morphing airfoil are studied analytically and numerically. The relationships for the unsteady lift coefficient as a function of the geometry parameters for the morphing airfoil are discussed. The influences of different free-stream Mach, the angle of attack and morphing acceleration on aerodynamic characteristics during the reciprocating deformation are obtained.
In summary, the study for unsteady aerodynamic characteristics of two-dimensional morphing Joukowski airfoil by theoretical analysis and numerical calculation is performed under the incompressible, subsonic and supersonic flow conditions for inviscid fluid. The research of this work is expected to have a practical help to the engineering practice in the future.
引文
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