An Experimental Model and Method for Acquiring Frontal Edge Heat Flux

Abstract

The invention provides a test model and method for obtaining the heat flux density of the leading edge, including a wind tunnel test model and M modules, the wind tunnel test model digs a groove in the direction of the geometric centerline of the curved surface of the sharp leading edge, and the length of the groove is not less than that of the sharp leading edge The geometric centerline of the curved surface obtains the length of the spatial range of heat flow. The size of each module matches the size of the slot on the wind tunnel test model, and is installed in the slot along the centerline. The geometric centerline of the curved surface of the sharp front edge is along the module Holes are drilled at a certain distance, and integral heat flow sensors are installed in the holes. The position of the holes on any one module is staggered with the positions of the holes on the other M‑1 modules. The invention realizes dense measurement at an equivalent interval of 0.2 millimeters at the sharp leading edge by means of multi-module "block combination and staggered arrangement" of the test model, and solves the problem of insufficient spatial resolution of the heat flow sensor in the wind tunnel heat measurement test.

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.

Images