Wing test element for ice wind tunnel of anti-icing system for aircraft wing

Abstract

The invention discloses a wing test element for an ice wind tunnel of an anti-icing system for an aircraft wing. The wing test element comprises a shell, an anti-icing cavity and a test flute pipe, wherein the shell is formed by performing sweepback stretching on a critical cross-section; the critical cross-section is defined in the following mode: a possible serious icing area is determined according to the water droplet impingement property of an external flow field of the aircraft wing, the most possible serious icing area is determined according to thermal power distribution of a flute pipe in the aircraft wing, and a chordwise airfoil along the airflow in the most possible serious icing area is defined as the critical cross-section; the sweepback stretching is that the critical cross-section is stretched into a test wing and the aircraft wing leading edge wire in the wing unfolding direction of the test wing and a straight line vertical to the critical cross-section form a sweepback angle; the anti-icing cavity is formed in the shell, and structural parameters of the anti-icing cavity are configured to be the same as those of an anti-icing cavity of a true aircraft wing at a standard position; and the test flute pipe is arranged in the anti-icing cavity, and related parameters of the test flute pipe are configured to be the same as parameters of a flute pipe of the true aircraft wing at the standard position.

Description

technical field [0001] The invention relates to an airfoil test piece used for an ice wind tunnel test of an aircraft wing anti-icing system and a method for determining the airfoil surface thereof. Background technique [0002] The wing anti-icing system of civil aircraft provides safety guarantee for the flight of the aircraft under icing weather conditions, and provides sufficient heat source for the wing, the key component of the aircraft to generate lift, so as to avoid icing on the surface of the wing and affecting the aerodynamics of the wing shape. [0003] In the research and development process of the wing anti-icing system, it is an indispensable link to use various tests to verify the performance of the system. With the continuous development of test and measurement technology, ice wind tunnels that simulate icing clouds are gradually being used to verify the performance of aircraft wing anti-icing systems. [0004] Usually, in the research and development proc...

AI Technical Summary

Problems solved by technology

[0007] If a 3D full-scale airfoil test piece is used for the test, due to the size limitation of the ice wind tunnel, only a certain section along the span of the real wing can be selected for testing. Due to the influence of the wall surface of the ice wind tunnel, the results of the external flow field of the entire airfoil test piece will greatly deviate from the real situation, which is difficult to provide guarantee for the performance verification of the wing anti-icing system

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