A combined pFFT-multipole tree code, unsteady panel method with vortex particle wakes

2007 ◽  
Vol 53 (8) ◽  
pp. 1399-1422 ◽  
Author(s):  
David J. Willis ◽  
Jaime Peraire ◽  
Jacob K. White
Keyword(s):  
Panel Method ◽  
Unsteady Panel Method ◽  
Vortex Particle

Unsteady panel method for flows with multiple bodies moving along various paths

AIAA Journal ◽  
1994 ◽  
Vol 32 (1) ◽  
pp. 62-68 ◽  
Author(s):  
Thomas F. Richason ◽  
Joseph Katz ◽  
Dale L. Ashby
Keyword(s):  
Panel Method ◽  
Unsteady Panel Method

scholarly journals SIMULATION OF A MANEUVERING AIRCRAFT USING A PANEL METHOD

2021 ◽  
Vol 61 (2) ◽  
pp. 378-390
Author(s):  
Pavel Schoř ◽  
Martin Kouřil ◽  
Vladimír Daněk
Keyword(s):  
Reasonable Agreement ◽  
Panel Method ◽  
Aerodynamic Forces ◽  
Local Pressure ◽  
First Order ◽  
Unsteady Panel Method ◽  
Flight Parameters ◽  
Time Required ◽  
Control Surfaces ◽  
Load Evaluation

We present a method for numerical simulations of a maneuvering aircraft, which uses a first-order unsteady panel method as the only source of aerodynamic forces and moments. By using the proposed method, it is possible to simulate a motion of an aircraft, while the only required inputs are geometry and inertia characteristics, which significantly reduces the time required to start the simulation. We validated the method by a comparison of recordings of flight parameters (position, velocities, accelerations) from an actual aerobatic flight of a glider and the results obtained from the simulations. The simulation was controlled by deflections of control surfaces recorded during the actual flight. We found a reasonable agreement between the experimental data and the simulation. The design of our method allows to evaluate not only the integral kinematic quantities but also instant local pressure and inertia loads. This makes our method useful also for a load evaluation of an aircraft. A significant advantage of the proposed method is that only an ordinary workstation computer is requiredto perform the simulation.

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