Average angle of attack adjustment mechanism of continuous transonic wind tunnel airfoil profile dynamic experiment

Abstract

The invention provides an average angle of attack adjustment mechanism of a continuous transonic wind tunnel airfoil profile dynamic experiment. A first oscillating shaft is located at one end of a wind tunnel rotating window, and a second oscillating shaft and a third oscillating shaft are located at the other end of the wind tunnel rotating window. An average angle of attack adjustment disk is located on the second oscillating shaft, and an oscillating shaft adjustment disk is located on the third oscillating shaft. The average angle of attack adjustment mechanism provided by the invention overcomes the errors of an indirect adjustment mode of the traditional mechanism in machining and assembly processes, and the verticality of the axis of the oscillating shaft and a side wall of a windtunnel, a gap between the oscillating shaft and a rotating window through hole and the jump between an end face of a rotating shaft and the rotating window can be controlled more accurately in the installation of the oscillating shaft, thereby effectively reducing the friction loss of the oscillating shaft and improving the duality of the airfoil profile dynamic experiment; and the average angle of attack is adjusted by rotating the relative position of a flange plate of the average angle of attack, and the problems of small adjustment range of the traditional mechanism and few coverage angleswithin the adjustment range are overcome.

Description

technical field [0001] The invention relates to the field of aerospace wind tunnel experimental equipment, in particular to a continuous transonic wind tunnel airfoil dynamic experiment average angle of attack adjustment mechanism. Background technique [0002] Helicopters are different from traditional fixed-wing aircraft in that they can take off and land in a relatively narrow area, do not need special airports and runways, can hover in the air, and can fly in all directions. Due to this special flying mode, Helicopters have been widely used in both military and civilian fields, but with the deepening of helicopter applications, people have put forward higher requirements for the flight performance and safety performance of helicopters. [0003] When the rotor system is working, due to the relatively high speed of the forward blade relative to the incoming flow, the lift force generated is also large, while the relative speed of the backward blade is relatively small, so ...

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Problems solved by technology

[0007] In order to overcome the deficiencies in the prior art that exist in the existing technology, such as large adjustment accuracy error, few adjustable angles, and inability to meet the requirements of continuous high-speed wind tunnel airfoil dynamic experiments, the present invention proposes a continuous transonic wind tunnel airfoil dynamic Experimental average angle of attack adjustment mechanism

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