Low Speed Wind Tunnel Test Method and Structural Function Verification of Variable Camber Wing Leading Edge Full Scale Prototype

In order to verify the structural function of the civil aircraft variable camber wing leading edge full-scale prototype under real wind load, the test method was studied by using the large-scale low-speed wind tunnel FL-10. Combined with the structural characteristics of the prototype, two-side support style with elliptical end plates was selected. Based on the principle of two-dimensional optical deformation measurement, an optical measurement system capable of accurately measuring the leading edge surface deformation was built. The structural function verification of the full-scale prototype was completed from two aspects of deformation and maintenance. The results show that: for the prototype with a length of 4.3 m and a width of 2.7 m, the leading edge load equivalent to the actual take-off and landing flight state can be obtained. The chordwise proportion of the leading edge that can be measured is 93%, and the displacement measurement accuracy is 0.10 mm, which can meet the structure functional verification requirements. Through the wind tunnel test, it is verified that the variable camber leading edge can accurately achieve the target shape deformation under wind load. The relative deformation of the maximum deflection shape is less than 0.5%, and the spanwise relative deformation deviation is less than 1%. The relative deformation of the intermediate deflection shape do not exceed 3%. The relative deformation of the maximum deflection shape caused by the angle of attack is less than 2%, and that caused by the wind speed is less than 0.2%.