Abstract
Frequent flight conflicts will be observed as the number of aircrafts increases, and such conflicts will cause unprecedented challenges in flight safety; thus, the flight characteristics of small aircrafts under the wake flow of a large airliner should be thoroughly analyzed. Combined with the sliding mesh technique, a computational fluid dynamics (CFD) method is proposed in this paper to simulate three wake flow patterns, i.e., wingtip vortex, jet flow, and propeller slipstream, and then, the static and dynamic derivatives that represent the stability of the fly wing under the wake flow are identified by using the least squares method. The results demonstrate that both the steady and unsteady aerodynamics of the fly wing are affected by wake flows: wingtip vortices increase the lift-to-drag ratio and considerably change the dynamic damping; jet flow reduces both the static and dynamic damping; and propeller slipstream leads to slow variations in the dynamic damping and decreases in the lift-to-drag ratio.
Highlights
Improvements in aeronautical techniques and increased demand have led to an increasing number of flight vehicles in various fields
The present study proposes a method that combines highfidelity computational fluid dynamics (CFD) and a sliding mesh technique to assess the static and dynamic aerodynamics of the fly wing configuration [18, 19] under the effects of wingtip vortices, jet flow, and propeller slipstream, and the corresponding derivatives are identified to evaluate the stability of the aircraft
A novel CFD method based on a sliding mesh technique was proposed to calculate the static and dynamic aerodynamics of three wake flow patterns, and the static and dynamic stability derivatives were identified by using the least squares method
Summary
Improvements in aeronautical techniques and increased demand have led to an increasing number of flight vehicles in various fields. Air traffic systems will be tasked with addressing this increased congestion, and frequent flight conflicts will place unprecedented pressure on control systems and threaten flight safety. One of the negative phenomena related to flight congestion is the impact of the wake of the front aircraft on the rear aircraft, and this phenomenon has caused several air crashes in the history of aircraft. The wake effect [1] should be considered for military aircraft, such as during aerial refueling, because accurate control of the refueling aircraft in the wake flow of a large aerial tanker is a challenging task. To ensure flight safety and improve the task completion efficiency, the effect of a wake on the aerodynamics of small aircraft should be analyzed in detail
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