Static aeroelasticity wind tunnel test half-model system and test method

Abstract

The invention provides a static aeroelasticity wind tunnel test half-model system and test method. The static aeroelasticity wind tunnel test half-model system comprises a half-model arranged in a wind tunnel and a measuring device arranged at the outside of a wind tunnel wallboard; the half-model comprises a main body and a pneumatic airfoil; the main body is provided with a thickening portion atone side, towards the wind tunnel wallboard, of a symmetric plane; the thickening portion is closely adjacent to the wind tunnel wallboard; the thickening portion is used for enabling the distance between the symmetric plane and the wind tunnel wallboard to be greater than or equal to the thickness of a boundary layer of the wind tunnel; and the measuring device is used for measuring the static aeroelasticity effect on the pneumatic airfoil. According to the static aeroelasticity wind tunnel test half-model system and test method, the aerodynamic interference with the half-model by the boundary layer on a tunnel wall and gap fluid channeling can be effectively and respectively isolated and eliminated, and the practicality and the economic property are high.

Description

technical field [0001] The invention relates to the technical field of wind tunnel testing, in particular to a static aeroelastic wind tunnel test semi-model system and a test method. Background technique [0002] Static aeroelasticity is a phenomenon in which an aircraft undergoes elastic deformation under the action of aerodynamic force, which causes its aerodynamic characteristics to change. Static aeroelasticity has a great influence on the aerodynamic characteristics of the aircraft. It may change the geometric shape of the aircraft, affect the efficiency of the rudder surface and the stability of the aircraft, and cause the phenomenon of wing surface damage due to the divergence of the lifting surface. Therefore, it is necessary to study the static aeroelasticity of aircraft through experiments. The static aeroelasticity of the aircraft can be studied through the high-speed wind tunnel test. Since the flow field around the aircraft is left-right symmetrical, a semi-mo...

AI Technical Summary

Problems solved by technology

The half-model test method has obvious shortcomings: since the half-model is installed near the wind tunnel wall on the longitudinal symmetry plane, the low-speed, low-energy airflow in the boundary layer of the tunnel wall will affect the test results of the half-model, and the force test , there is a certain gap between the longitudinal symmetry plane of the model and the cave wall, there must be air flow in the gap, and this channeling will also affect the test results

[0004] In the block method, since there is a gap of a certain width between the symmetry plane of the half model 11 and the block 13, the channeling flow in the gap will interfere with the flow characteristics around the half model 11, resulting in distortion of the test results

Images