Simulation of Vortex Wake Impact on a General-Aviation Aircraft Model in a Wind Tunnel Using the Airfoil Lattice

Paper #:
  • 965545

Published:
  • 1996-10-01
Citation:
Mikhailov, Y., "Simulation of Vortex Wake Impact on a General-Aviation Aircraft Model in a Wind Tunnel Using the Airfoil Lattice," SAE Technical Paper 965545, 1996, https://doi.org/10.4271/965545.
Author(s):
Pages:
11
Abstract:
In the TsAGI T-103 wind tunnel, an effective method has been tested for simulating the impact of the vortex wake forming behind a heavy aircraft during take-off and landing operations on aerodynamic characteristics of the following aircraft flying along a trajectory close to the vortex wake axis. For simulation an airfoil lattice with a differential deflection of the sections along the span is used. The lattice is mounted at the wind tunnel nozzle exit. Investigations of flow structure and tests of a general-aviation aircraft model has shown that the airfoil lattice creates in the test section flow deflections which are equivalent of wake influence formed by the B-747 airplane in landing configuration on distance from 500m and more.
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