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121.
N. B. Il’inskii R. F. Mardanov 《Computational Mathematics and Mathematical Physics》2007,47(10):1712-1719
The problem is solved of designing a symmetric airfoil with upstream blowing opposite to subsonic irrotational steady flow of an inviscid incompressible fluid. The solution relies on Sedov’s idea of a stagnation region developing in the neighborhood of the stagnation point. An iterative solution process is developed, and examples of airfoils are constructed. The numerical results are analyzed, and conclusions are drawn about the effect of blowing parameters on the airfoil geometry and the resultant force acting on the airfoil. 相似文献
122.
D. F. Abzalilov 《Computational Mathematics and Mathematical Physics》2007,47(2):293-300
The problem of lift maximization for a smooth contour of given length placed in a flow near a screen is analyzed. The distance between the contour and the screen is assumed to be given. Optimal contours are constructed, and the lift coefficient is derived as a function of the contour-screen separation. The results can be useful as accurate upper bounds for the lift coefficient of actual ekranoplan airfoils. 相似文献
123.
Navier-Stokes analysis of a circulation control airfoil 总被引:2,自引:0,他引:2
The two-dimensional, compressible, mass-averaged Navier-Stokes equations are used to investigate flows about a typical circulation
control airfoil. The governing equations are solved using the implicit approximate-factorization algorithm of Beam-Warming
with a modified algebraic eddy viscosity model. Results are compared with experimental data, and excellent agreement is obtained.
The effects of different jet momentum coefficients and angles of attack on the flow are studied. The mechanism of genenating
large lift by circulation control is discussed. 相似文献
124.
125.
The preconditioning technique can address the stiffness of a low Mach number flow, while its stability is poor. Based on the
conventional preconditioning method of Roe's scheme, a low-diffusion scheme is proposed. An adjustable parameter is introduced
to control numerical dissipation, especially over the dissipation in the boundary layer and extremely in a low speed region.
Numerical simulations of the low Mach number and low Reynolds number flows past a cylinder and the low Mach number and high
Reynolds number flows past NACA0012 and S809 airfoils are performed to validate the new scheme. Results of the three tests
well agree with experimental data, showing the applicability of the proposed scheme to low Mach number flow simulations. 相似文献
126.
The effects of a harmonically deflected trailing-edge flap, actuated at different start times and amplitudes but with frequency different from the airfoil motion, on the aerodynamic loads of an oscillating NACA 0015 airfoil were investigated experimentally at Re=2.51×105. Both in-phase and 180° out-of-phase flap deflections, relative to the airfoil motion, were tested. The results show that there was a large change in the hysteretic behavior of the dynamic load loops, and that the formation and detachment of the leading-edge vortex (LEV) were not affected by the flap motion, while the low pressure signature of the vortex was affected by the flap actuation start time. The later the flap actuation the larger the change in the strength of the LEV. The present flap control scheme was also found to be as effective as that achieved by a pulsed ramp flap motion, but with a reduced number of control parameters. 相似文献
127.
128.
风力机翼型挥舞摆振非定常气动特性分析 总被引:2,自引:0,他引:2
参考实际运行状态下的风力机翼型,应用动网格并采用kω-SST湍流模型对NREL S809翼型在Re=1×106情况下的翼型振荡进行了数值模拟,同时分析了挥舞、摆振及二者耦合振动对风力机翼型气动性能的影响.结果表明:相同振幅和频率下,翼型挥舞比摆振引起的气动力波动大得多;翼型未达到失速时,翼型吸力面的流动分离可以使翼型获得额外的升力;挥舞的振幅或频率较大时,翼型会发生失速,且来流攻角越大,挥舞使得翼型更易发生失速;在挥舞-摆振耦合引起的翼型气动力变化中,挥舞起主导作用. 相似文献
129.
130.
The results of computational fluid dynamics (CFD) simulations in two and three spatial dimensions are compared to pressure measurements and particle image velocimetry (PIV) flow surveys to assess the suitability of numerical models for the simulation of deep dynamic stall experiments carried out on a pitching NACA 23012 airfoil. A sinusoidal pitching motion with a 10° amplitude and a reduced frequency of 0.1 is imposed around two different mean angles of attack of 10° and 15°. The comparison of the airloads curves and of the pressure distribution over the airfoil surface shows that a three-dimensional numerical model can better reproduce the flow structures and the airfoil performance for the deep dynamic stall regime. Also, the vortical structures observed by PIV in the flow field are better captured by the three-dimensional model. This feature highlighted the relevance of three-dimensional effects on the flow field in deep dynamic stall. 相似文献