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Advances in Aircraft and Spacecraft Science
  Volume 8, Number 2, March 2021, pages 151-167
DOI: http://dx.doi.org/10.12989/aas.2021.8.2.151
 
open access

Stall in ground effect using the unsteady vortex lattice method with Kirchhoff-based correction
Carlos A. Neves and Pedro J. Boschetti

 
Abstract
    The goal of this research is to evaluate the stall behavior of a high aspect ratio rectangular wing in ground effect using an unsteady vortex-lattice method with a Kirchhoff-based correction (UVLM-K), including how the lift coefficient achieved in stall is affected by dynamic ground effect. A flow separation algorithm based on the Kirchhoff-Helmholtz theory and a flow separation model presented by Fischenberg are applied. The code was validated using experimental data from previously published works. The stall behavior of a rectangular wing of aspect ratio of 8.587 formed with a NACA 4415 airfoil section was studied in static and dynamic ground effect. To obtain the empirical data required by the UVLM-K, the NACA4415 airfoil was simulated at fixed height aboveground using a finite-volume code solver. The wing simulation results have shown that the lift coefficient achieved by the wing in stall for takeoff and flare maneuvers are lower than those estimated at a fixed height above the ground. It can be concluded, based on the results obtained herein, that the stall behavior of a wing in dynamic ground effect depends on the history of the maneuver.
 
Key Words
    unsteady aerodynamics; stall prediction; ground effect; computational fluid dynamics; take-off and landing; Kirchhoff flow theory
 
Address
Carlos A. Neves: Department of Mechanical Engineering, Universidad Simón Bolívar, Sartenejas Valley, Caracas 1080-A, Venezuela

Pedro J. Boschetti: Department of Industrial Technology, Universidad Simón Bolívar, Camuri Valley, Naiguatá 1163, Venezuela
 

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