| 講演要旨： |
In the process of aircraft development numerical approaches are
gaining more and more importance. Not only steady flight conditions
need to be modelled but also dynamic derivatives and last but not
least realistic flight maneuvers. At DLR a numerical simulation
framework is under development for calculating a freely flying
maneuvering delta-wing aircraft. In order to obtain a data base for
validating the simulation framework ground-based simulations of
complex maneuvers of an aircraft have been performed in the open test
section of the 2.85 × 3.20 m2 low-speed atmospheric wind
tunnel NWB of the German-Dutch Wind Tunnels DNW. A fully equipped
wind tunnel model of the X-31 was developed and built to a scale of
about 1/7.25. The model is equipped with eight remotely controlled
flaps that are moved by eight servo motors. Dynamic surface
pressures have been measured by miniature piezo-resistive pressure
sensors located at 60% and 70% chord length on the upper surface of
the delta wing and on the leading edge flaps. Forces and moments
were obtained by a 6-component strain gauge also included in the main
part of the model. In the wind tunnel a newly installed novel test
rig with six degree of freedoms was used for the first time for
moving the model. The complex three-dimensional motion of the model
is controlled by an optical position tracking system. In addition to
pitching, rolling and yawing motions also real flight maneuvers, for
example corresponding with steady-heading sideslip test points, were
simulated. Both, the specific technical equipment of the model and
the novel six DOF test rig will be reviewed. Thereafter,
experimental results obtained will be discussed and compared with
numerical results.
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