A wind tunnel investigation was conducted to investigate the unsteady aerodynamic aspects of transonic Limit Cycle Oscillations (LCO) on fighter type aircraft wings. The first test, conducted with a wing body configuration with wing stores, was restricted to incidences below 10 deg. Test results are presented with the objective of obtaining unsteady pressure and forces necessary for identifying the aerodynamic nature of transonic LCO which is currently encountered on many fighter configurations. The wing panel was oscillated in pitch at amplitudes and frequencies typical of LCO for flow conditions in which significant shock-induced separation is encountered. Unsteady pressure data were obtained for the wing panel in terms of both harmonic components and time-histories to highlight the nonlinearities. Unsteady forces and moments measured on the wing panel as well as on each wing store were also obtained to indicate the level of contribution of each element to the overall unsteady wing loads for pitching motions.
Transonic Wind Tunnel Investigation of Limit Cycle Oscillations on Fighter Type Wings
1992
14 pages
Report
Keine Angabe
Englisch
Wind Tunnel Investigation of Transonic Limit Cycle Flutter
British Library Conference Proceedings | 1998
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