SIMULATION OF A MANEUVERING AIRCRAFT USING A PANEL METHOD
Keywords:Flight mechanics, aerodynamics, simulation, panel method, maneuvering aircraft.
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 required
to perform the simulation.
B. L. Stevens, F. L. Lewis, E. N. Johnson. Aircraft control and simulation: dynamics, controls design, and autonomous systems. John Wiley & Sons, 2015.
J. Roskam. Airplane flight dynamics and automatic flight controls. DARcorporation, 2003.
L. T. Nguyen. Simulator study of stall/post-stall characteristics of a fighter airplane with relaxed longitudinal static stability, vol. 12854. National Aeronautics and Space Administration, 1979.
J. Haider, C. H. Lee, A. Gil, et al. A first order hyperbolic framework for large strain computational solid dynamics in openfoam. In World Congress on Computational Mechanics and The Asia-Pacific Congress on Computational Mechanics, pp. 688–688. 2016.
P. Schor. Load State of an Aircraft with an Elastic Wing. Ph.D. thesis, Brno University of Technology, Technicka 2, Brno, 2018.
J. Katz, A. Plotkin. Low-speed aerodynamics, vol. 13. Cambridge university press, 2001. doi:10.1017/CBO9780511810329.
B. Maskew. Program VSAERO Theory Document: A Computer Program for Calculating Nonlinear Aerodynamic Characteristics of Arbitrary Configurations. NASA contractor report. National Aeronautics and Space Administration, 1987.
D. Ashby. Potential Flow Theory and Operation Guide for the Panel Code PMARC. National Aeronautics and Space Administration, 1999.
D. J. Willis. Implementing automatic-wake body intersections for full aircraft congurations in dirichlet panel methods. In 31st AIAA Applied Aerodynamics Conference, p. 2650. 2013.
D. J. Willis, J. Peraire, J. K. White. A combined pfft-multipole tree code, unsteady panel method with vortex particle wakes. International Journal for numerical methods in fluids 53(8):1399–1422, 2007.
G. Gennaretti, M. Bemardini. Novel boundary integral formulation for blade-vortex interaction aerodynamics of helicopter rotors. AIAA journal 2007. doi:10.2514/1.18383.
T. Cebeci, J. Shao, F. Kafyeke, E. Laurendeau. Computational Fluid Dynamics for Engineers: From Panel to Navier-Stokes Methods with Computer Programs. Springer, 2005. doi:10.1007/3-540-27717-x.
J. Bakunowicz, R. Meyer. In-flight wing deformation measurements on a glider. The Aeronautical Journal 120(1234):1917–1931, 2016. doi:10.1017/aer.2016.98.
V. Danek, M. Kouril, R. Sosovicka. Measurement of aerobatic flight characteristics. vol. 3. Czech Aerospace Research Centre, 2006.
F. T. Johnson, E. N. Tinoco, N. J. Yu. Thirty years of development and application of cfd at boeing commercial airplanes, seattle. Computers & Fluids 34(10):1115–1151, 2005.
I. Kroo. Nonplanar wing concepts for increased aircraft efficiency. ’VKI Lecture Series’ 2005.
N. N. Gavrilovic, B. P. Rasuo, G. S. Dulikravich, V. B. Parezanovic. Commercial aircraft performance improvement using winglets. FME Transaction 43(1):1–8, 2015. doi:10.5937/fmet1501001g.
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Copyright (c) 2021 Pavel Schoř, Martin Kouřil, Vladimír Daněk
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