Mach 6 Quiet Tunnel Laminar to Turbulent Investigation of a Generic Hypersonic Forebody
Mach 6 Quiet Tunnel Laminar to Turbulent Investigation of a Generic Hypersonic Forebody
复制标题
通用高超音速前体的 6 马赫安静隧道层流到湍流研究
DOI：
10.2514/6.2015-3575
复制
发表时间：
2015
影响因子：
3.7
通讯作者：
Brandon C. Chynoweth
中科院分区：
文献类型：
--
作者：
A. Durant;T. André;S. Schneider;Brandon C. Chynoweth
本文介绍了2015年4月在普渡大学波音/AFOSR马赫6安静风洞设施（BAM 6 QT）中对通用高超音速前体迎风侧进行的实验边界层转捩研究。在0 °和4 °攻角下，Reu= 11 x10 6 /m，在安静条件下流动完全为层流。在噪声条件下，即使用单位自由雷诺数除以6，也能观察到早期转捩锋（Reθ~200）。在安静条件下，当Rekk > 1000时，发现几个菱形粗糙度行程有效地行程层流边界层。温敏涂料（TSP）实现了热通量分布的全球测量和过渡前沿的检测。PCB传感器确认了边界层的状态：层流、湍流或过渡。在不同的压力比下，也收集了单个连续吹气的音速空气射流的转捩结果，给出了层流到湍流的阈值。
This paper presents an experimental boundary layer transition investigation of the windward side of a generic hypersonic forebody performed in April 2015 in the Boeing/AFOSR Mach 6 quiet tunnel facility at Purdue university (BAM6QT). At 0 and 4 degrees of angle of attack, Reu=11x10 6 /m, flow was fully laminar in quiet conditions. Under noisy conditions, an early transition front (Reθ~200) was observed, even when dividing the unit freestream Reynolds number by 6. In quiet conditions, several diamond-shaped roughness trips were found to efficiently trip the laminar boundary layer when Rekk > 1000. Temperature-Sensitive Paint (TSP) enabled a global measurement of the heat flux distribution and detection of the transition front. PCB sensors confirmed the state of the boundary layer : laminar, turbulent or transitional. Transition results with a single continuously blowing sonic air jet was also collected at various pressure ratios, giving the laminar to turbulent threshold.