Application of Pressure-Sensitive Paint for Determination of Dynamic Surface Pressures on a Rotating 65° Delta Wing and an Oscillating 2D profile in Transonic Flow
Application of Pressure-Sensitive Paint for Determination of Dynamic Surface Pressures on a Rotating 65° Delta Wing and an Oscillating 2D profile in Transonic Flow
复制标题
DOI：
10.1109/iciasf.2007.4380887
复制
发表时间：
2007-06
期刊：
影响因子：
--
通讯作者：
C. Klein;U. Henne;Werner Sachs;R. Engler;Yasuhiro Egami;V. Ondruš;U. Beifuss;Holger Mai
中科院分区：
文献类型：
--
作者：
C. Klein;U. Henne;Werner Sachs;R. Engler;Yasuhiro Egami;V. Ondruš;U. Beifuss;Holger Mai
利用基于压敏涂料（PSP）技术的光学压力测量系统，对三角翼模型和二维翼型模型的气动效应进行了可视化和测量。PSP技术可用于获得模型表面的绝对压力测量值，并通过科学级相机和图像处理技术定量评估气动流动现象。在这里，PSP技术被用于周期性和非定常流的研究：首先，在哥廷根的DNW-TWG跨音速风洞中测试了一个65度三角翼。一个特别设计的滚转装置使滚转率高达10赫兹。实验在攻角为alpha = 17°，Ma = 0.8时进行。由于三角翼的旋转是周期运动，因此可以采用锁相非定常PSP技术。在DNW-TWG与DLR气动弹性研究所合作进行的第二次风洞试验中，研究了俯仰振荡高达30 Hz的2d机翼廓形模型。实验在攻角α = 1.12°，Ma = 0.72时为0.6°。在这些实验中，采用锁相非定常和非定常PSP技术在一个风洞入口进行了压力测量。
Visualization and measurements of aerodynamic effects on a delta-wing model and a 2D-wing-profile model were conducted using an optical pressure measurement system, based on the pressure-sensitive paint (PSP) technique. The PSP technique can be used to obtain absolute pressure measurements on the surface of a model and in addition to evaluate quantitative aerodynamic flow phenomena by using scientific grade cameras and image processing techniques. The PSP technique has been used here for investigations of periodic and unsteady flows: first, a 65deg delta wing was tested in the transonic wind tunnel DNW-TWG in Gottingen. A specially designed roll apparatus enabled roll rates up to 10 Hz. The experiments were carried out at angles-of-attack up to alpha = 17deg at Ma = 0.8. Since the rotation of the delta wing is a periodic motion, the phase-locked unsteady PSP technique can be applied. In a second wind tunnel campaign in the DNW-TWG in collaboration with the DLR Institute of Aeroelasticity, a 2D-wing-profile model, which is pitch oscillating at up to 30 Hz, was investigated. The experiments were performed at angles-of-attack alpha = 1.12deg plusmn 0.6deg at Ma = 0.72. For these experiments pressure measurements were carried out in one wind tunnel entry by means of both phase-locked unsteady as well as unsteady PSP techniques.