The dynamic responses of asymmetric vortices over a slender body to a rotating tip
perturbation were investigated experimentally in a wind tunnel. A small rotating nose with an …

大迎角下飞行器的常规舵面处于机身/弹身的尾涡中, 偏航控制能力严重下降. 同时,
背风侧的非对称涡系导致压力非对称分布, 从而诱发出一个几乎与法向力同量级的侧向力 …

This paper describes a heuristic approach to feedback flow control and illustrates its use for
two flowfields: the flow around a tangent ogive at large angles of attack and the shear layer …

View Video Presentation: https://doi. org/10.2514/6.2021-2610. vid The aerodynamic
instability of the inclined slender cylindrical model (L/D= 11) with an ogive forebody is …

View Video Presentation: https://doi. org/10.2514/6.2021-1943. vid The flow over an inclined
slender axisymmetric cylinder (L/D= 11) with an ogive forebody is investigated …

The experimental data obtained from yaw-roll coupled wind tunnel tests are used for lateral-
directional departure prediction, by linearizing the β ̇ model to extract nominal dynamic …

Dynamically-controlled aerodynamic bleed across the segmented surface of the forebody of
a cylinder platform model at high angles of incidence (30⁰< α< 60⁰) is explored for …

At high angles of attack or low Reynolds number, aircraft wings or blades of helicopters or
even wind turbines may encounter separation of the ow which can eventually lead to …

Modeling of transient blowing actuation using Pulse Width Modulation on a dynamically pitching
NACA 0018 Airfoil Page 1 Modeling of transient blowing actuation using Pulse Width Modulation …

This numerical study is about the alleviation of the Phantom Yaw Effect on a pitching missile.
A pair of slit shaped side jets, so called aerostrakes is used to force a symmetric separation …