發(fā)布時間：2019-03-19 17:34

【摘要】：座頭鯨具有的前緣突起的肢狀胸鰭,為其撲食回轉(zhuǎn)提供強大的動力。受此生物學(xué)特性啟發(fā)。本文作者開展了以NACA634-021為基本翼型和相應(yīng)的仿生凹凸前緣翼型的氣動特性、流場特性以及凹凸前緣流動控制機理研究。在此基礎(chǔ)上,對典型的風(fēng)力機翼型DU40、DU18的仿生凹凸前緣流動控制進行了實驗研究和數(shù)值計算研究；同時對仿生凹凸前緣葉片和光滑葉片進行實驗研究。針對以NACA634-021翼型為基型的光滑翼段和凹凸前緣翼段模型,在0�！�90°攻角,采用三分量測力天平和粒子圖像測速儀(PIV)于直流風(fēng)洞中分別測量升力、阻力、俯仰力矩等翼型氣動特性和流速、渦量、邊界層等流場特性,開展仿生凹凸前緣流動控制的有效性和作用機理的實驗研究。實驗結(jié)果表明：與光滑翼段相比,凹凸前緣翼段的失速特性更為平緩,失速后氣動特性有明顯改善,其中升力系數(shù)提高可達18%,升阻比可增加12%,阻力系數(shù)減小10%,在30°～80°高攻角區(qū)內(nèi)凹凸前緣仍然具有一定的效果；通過分析,凹凸前緣翼型對失速控制的作用機理在于：當(dāng)氣流繞過凹凸前緣后,氣流被引導(dǎo)環(huán)繞凸峰運動,在每個凸包的兩側(cè)產(chǎn)生一對反向旋轉(zhuǎn)的流向渦結(jié)構(gòu),該渦結(jié)構(gòu)作用范圍不僅僅局限在邊界層內(nèi),加強了邊界層內(nèi)部和外部勢流的動量交換,進而增強了翼型抵御逆壓梯度的能力,降低了吸力面的負壓梯度,推遲了流動分離,失速得以延緩。同時分析了流向渦環(huán)量的變化趨勢,在攻角17°～25°之間其環(huán)量值在變化很小,使得翼型失速平緩。依據(jù)凹凸前緣流動控制機理,對凹凸前緣的有效高度與邊界層heffc/δ的比值進一步分析,發(fā)現(xiàn)heffc/δ小于1,其范圍在0.1-0.5之間能有效改變翼型的失速特性與微小渦流發(fā)生器作用相似。通過DU40和仿生凹凸前緣DU40-25wavy、DU40-11wavy和1DU18和仿生凹凸前緣DU18-25wavy、DU18-11wavy的氣動力特性實驗研究表明,在高攻角區(qū)域凹凸前緣翼型都能提高升力系數(shù),在低攻角區(qū)域11wavy翼型更有優(yōu)勢氣動升力相比光滑減小幅度較小。通過計算DU40和仿生凹凸前緣DU40-25wavy、DU40-11wavy和DU18和仿生凹凸前緣DU18-25wavy、DU18-11wavy在低攻角區(qū)域和高攻角區(qū)域的流場和壓力系數(shù)分布表明,凹凸凸起對于壓力系數(shù)的分布有較大的影響,在低攻角區(qū)域由于凹凸前緣的影響較弱壓力差提高幅度較小,在高攻角區(qū)域由于凹凸前緣引起的流向渦強度增大,壓力系數(shù)在翼型的前緣差值增大,提高了升力系數(shù)。另夕11wavy翼型提高幅度較大,表現(xiàn)了更優(yōu)異的氣動性能。在雙葉片風(fēng)機實驗臺上進行了光滑葉片和凹凸前緣葉片的風(fēng)洞試驗,結(jié)果表明：對于凹凸前緣葉片,在來流風(fēng)速和尖速比分別與光滑葉片保持相同的情況下,凹凸前緣葉片扭矩增大15.6%,推力減小9.7%,功率系數(shù)提高可達到22%。
[Abstract]:Humpback whales have a protuberant limb-shaped pectoral fin that provides a powerful force for flapping and turning. Inspired by this biological characteristic. In this paper, the aerodynamic characteristics, flow field characteristics and flow control mechanism of NACA634-021-based airfoils and corresponding bionic concave-convex front airfoils are studied. On this basis, the flow control of bionic concave-convex leading edge of typical wind turbine airfoil DU40,DU18 is studied experimentally and numerically, and the bionic concave-convex front blade and smooth blade are also studied experimentally. For the smooth airfoil and concave-convex front wing models based on NACA634-021 airfoil, the lift and resistance were measured in a DC wind tunnel using a three-component force balance and a particle image velocimeter (PIV) at an angle of attack of 0. 0 擄and a particle image velocimeter (PIV), respectively, at an angle of attack of 0. 0. 90 擄. The aerodynamic characteristics, velocity, vorticity and boundary layer characteristics of pitching moment equal airfoil are studied. The effectiveness and mechanism of flow control of bionic concave and convex leading edge are studied experimentally. The experimental results show that the stall characteristics of concave and convex front flanks are more smooth than that of smooth airfoils, and the aerodynamic characteristics are obviously improved after stall. The lift coefficient increases by 18%, the lift-drag ratio increases by 12%, and the drag coefficient decreases by 10%. In the area of 30 擄~ 80 擄high angle of attack, the concave and convex leading edge still has certain effect. According to the analysis, the mechanism of the airfoil acting on the stall control is that when the air flows around the convex front, the air flow is guided around the convex peak, and a pair of reverse rotating flow vortices are produced on both sides of each convex envelope. The scope of the vortex structure is not only confined to the boundary layer, but also enhances the momentum exchange between the inner and outer potential flows in the boundary layer, and then enhances the airfoil's ability to resist the inverse pressure gradient, reduces the negative pressure gradient on the suction surface, and delays the flow separation. The stall was delayed. At the same time, the variation trend of the flow vorticity is analyzed. The value of the torus varies little between the angle of attack 17 擄~ 25 擄, which makes the airfoil stall smooth. Based on the flow control mechanism of the bump front, the ratio of the effective height of the bump front to the boundary layer heffc/ 未 is further analyzed. It is found that the heffc/ 未 is less than 1, The range between 0.1 and 0.5 can effectively change the stall characteristics of airfoils, which is similar to the action of micro eddy current generator. The aerodynamic characteristics of DU40, bionic bump leading edge DU40-25wavy,DU40-11wavy and 1DU18 and bionic bump leading edge DU18-25wavy,DU18-11wavy are experimentally studied. The results show that the lift coefficient of the airfoil can be improved in the high angle of attack region. In the low angle of attack region, the aerodynamic lift of the 11wavy airfoil is more dominant than that of the smooth reduction of aerodynamic lift. The distributions of flow field and pressure coefficient of DU40 and bionic bump leading edge DU40-25wavy,DU40-11wavy and DU18 and bionic bump leading edge DU18-25wavy,DU18-11wavy in low angle of attack region and high angle of attack region are calculated. The bump has a great influence on the distribution of pressure coefficient. In the low angle of attack region, the pressure difference increases slightly due to the weak influence of the front edge of bump, and in the region of high angle of attack, the intensity of flow vorticity increases due to the leading edge of bump. The pressure coefficient increases at the leading edge of the airfoil and increases the lift coefficient. On the other hand, the improvement range of 11wavy airfoil is larger, and it shows better aerodynamic performance. Wind tunnel tests of smooth blades and concave-convex front blades were carried out on a two-blade fan test rig. The results show that for concave-convex front blades, the inlet wind speed and tip-velocity ratio are the same as those of smooth blades, respectively. The torque of the front blade increases by 15.6%, the thrust decreases by 9.7%, and the power coefficient increases by 22%.
【學(xué)位授予單位】：中國科學(xué)院研究生院(工程熱物理研究所)
【學(xué)位級別】：博士
【學(xué)位授予年份】：2014
【分類號】：TK83;TB17

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