The objective of this work is to study the feasibilty of using acoustic waves as a means for suppressing the flutter instability of a typical section in transonic flow. A high-resolution upwind TVD (total variation diminishing) flow solver of acoustic accuracy was first constructed and validated on a dynamic mesh system. The geometric conservation law was implemented consistently with the physical conservation law via a suitable defined cell boundary speed. This specially developed structure/fluid/acoustic solver was then integrated in the time domain to study whether flutter can be suppressed using active acoustic excitations. Flutter suppression was achieved in the transonic region when an appropriate feedback control law aws used. Large-amplitude limit cycle type oscillation in a transonic flow was also simulated. It was found that the present acoustic control technique can only be effective when the amplitude of the oscillation is small in accordance with previous findings obtained in a low-speed wind-tunnel test.
Transonic flutter suppression using active acoustic excitations
Flatterschwingungs-Unterdrückung in transsonischer Strömung mit Hilfe aktiver Schallanregung
AIAA Journal ; 33 , 4 ; 694-702
1995
9 Seiten, 15 Bilder, 28 Quellen
Aufsatz (Zeitschrift)
Englisch
Schwingungsdämpfung , Tragflügel , Flattern , transsonische Strömung , Schallsender , Schallwelle , Instabilität , Schwingungsverhalten , Maschennetz , geometrische Form , mathematisches Modell , Differenzialgleichung , Integralgleichung , akustische Rückkopplung , Steuerungs- und Regelungssystem , Grenzwert , Scheitelwert , Vergleichsmessung , Windkanal , Aerodynamik , Randbedingung , NACA-Profil , Software , Auftrieb , Druckverteilung
Transonic Flutter Suppression Using Active Acoustic Excitations
Online Contents | 1995
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