飞机全动平尾颤振特性风洞试验

doi:10.7527/S1000-6893.2014.0250

Abstract

Abstract:

Flutter wind tunnel test is the main technique in the flutter design process for the high maneuver aircraftall-movable horizontal tail. The low-speed flutter model of an all-movable horizontal tail has two kinds of configurations during wind tunnel test (single horizontal tail and horizontal tail with fixed rear fuselage). In low-speed wind tunnel, the basic flutter mode of the horizontal tail and the aerodynamic influence of the rear fuselage are investigated and verified. A semi-span dynamic scaled flutter model is used in transonic wind tunnel. The effect of Mach number and the aerodynamic influence of wing on the flutter boundary are investigated and verified. In this paper, details of flutter models' design are shown, and the wind tunnel test results indicate full flutter characteristics of the all-movable horizontal tail. Especially in transonic flutter wind tunnel test, the effect of mass parameter (Newton number) on flutter boundary is investigated using flutter model with different mass overload factors. Wind tunnel test results show that the flutter characteristic of the all-movable horizontal tail must consider the rear fuselage elastic support. Different configurations of flutter model are used to consider the influences of fuselage, wing and vertical fin. Transonic flutter model has to consider the mass overload factor. In general, all the flutter characteristics for the all-movable horizontal tail obtained through wind tunnel test could be taken as a reference in other aircraft design.

Key words: flutter, all-movable horizontal tail, wind tunnel test, scaled model, transonic wind tunnel, low-speed wind tunnel

CLC Number:

QIAN Wei, ZHANG Guijiang, LIU Zhongkun. Flutter characteristics for aircraft all-movable horizontal tail through wind tunnel test[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(4): 1093-1102.

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Flutter characteristics for aircraft all-movable horizontal tail through wind tunnel test

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