Supersonic-speed wind tunnel test section regulating device with angle adjustment function

Abstract

The invention discloses a supersonic-speed wind tunnel test section regulating device with the angle adjustment function and belongs to the field of wind tunnel test device design. The device includes a frame, an elastic beam, a hinge shaft, a fixed adjusting piece, a transition adjusting piece, a rotating adjusting piece, an ejector rod, an arc-shaped guide rail, a roll ball screw rod module, a servo motor, a reducer, a pull wire sensor and the like. A rail body of the arc guide rail is installed on the transition adjusting piece fixedly connected with the frame, a slider of the arc-shaped guide rail is connected with the rotating adjusting piece, the ejector rod is driven by means of a linear motion mechanism composed of the servo motor, the speed reducer and the roll ball screw rod module to walk, the rotation of the adjusting pieces is achieved, and oblique shock waves with the continuously variable shock wave angle is generated. The device has the function of accurately adjusting a wind tunnel flow field, can be applied in shock wave reflection and continuously variable Maher number research projects, can also be applied in pressure measuring, air inlet channel measuring and other supersonic-speed wind tunnel special tests, and effectively expands the capacity of the wind tunnel test.

Description

technical field [0001] The invention relates to a supersonic wind tunnel test section adjustment device with an angle adjustment function, which can be used for supersonic wind tunnel special test items such as shock wave reflection, continuously variable Mach number, pressure measurement, and air intake, and belongs to the design field of wind tunnel test devices . Background technique [0002] As a basic physical phenomenon of aerodynamics, shock wave has important physical significance and academic research value. As an important research field of aerodynamics, shock wave reflection phenomenon has been widely concerned in physics research. [0003] Figure 1(a) ~ Figure 1(f) is the change of the incoming flow Ma1 and the shock wave at the head of the wedge in the two-dimensional flow field. Figure 1(a) shows that when the incoming flow Ma1 just exceeds the speed of sound, an isolated shock wave appears in front of the wedge ; Figure 1(b) shows that the speed of Ma1 conti...

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Problems solved by technology

This method has shortcomings. The first is that the Mach number interval of the supersonic flow is at least 0.25, which has not yet reached the Mach number step accuracy required for the study of the shock reflection problem; the second is that the change of the wedge angle δ of the model is limited. The mechanism of continuously changing the wedge angle δ with a step span is limited by the model volume and cannot be realized

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