Test model and method for acquiring heat flux density of leading edge

Abstract

The invention provides a test model and method for acquiring the heat flux density of a leading edge. The test model comprises a wind tunnel test model and M modules. The wind tunnel test model is grooved in the geometric center line direction of a sharp leading edge curved surface. The length of the groove is not less than that of the spatial range of heat flow acquisition along the geometric center line of the sharp leading edge curved surface. The size of each module is matched with the size of the groove in the wind tunnel test model, and the modules are installed in the groove along the center line. Holes are punched in the modules at certain intervals along the geometric center line of the sharp leading edge curved surface, integrated heat flow sensors are installed in the holes, andthe positions of the holes in any module and the positions of the holes in the other M-1 modules are staggered. According to the invention, dense measurement with an equivalent interval of 0.2mm is realized at the sharp leading edge in a multi-module block combination and staggered arrangement mode of the test model, and the problem of insufficient spatial resolution of the heat flow sensors in the wind tunnel heat measurement test is solved.

Description

technical field [0001] The invention belongs to the technical field of wind tunnel tests for high-speed aircraft, and in particular relates to a test model and method for obtaining heat flux density at a complex sharp leading edge disturbed by shock waves. Background technique [0002] When the aircraft moves at high speed in the atmosphere, due to surface friction and shock wave compression, the gas on the surface of the aircraft will generate a lot of heat. This phenomenon of heat generated due to the high-speed relative motion of objects in the atmosphere is called aerodynamic heating. The sharper the object, the more severe the aerodynamic heating it receives. The size of various sharp leading edges such as the leading edge of the fuselage head of the aircraft, the leading edge of the engine inlet lip, and the leading edge of the wing / rudder is as small as millimeters, and at the same time, they are disturbed by shock waves in certain flight attitudes, making these The ...

AI Technical Summary

Problems solved by technology

The advantage of numerical simulation is that it can better display the flow field structure, but the disadvantage is that it is difficult to guarantee the accuracy of quantitative calculation results for complex problems such as sharp frontal heat flow disturbed by shock waves

The advantage of wind tunnel test measurement is that accurate heat flow data can be obtained through the heat flow sensor. However, due to the limitation of the test model processing technology and the installation space of the heat flow measurement sensor, the minimum distance between two adjacent heat flow measurement sensors is about 2 mm, and the excited The heat flow at the sharp leading edge of wave interference has drastic changes in the scale of a few tenths of a millimeter. The highest value of the most concerned heat flow is often not measured through wind tunnel tests, and the spatial resolution of the heat flow measurement test data is insufficient.

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