The present disclosure provides a method and system for calculating aerodynamic force of a wind turbine airfoil under different turbulence intensities. The method of the present disclosure includes: calculating a lift coefficient and a drag coefficient according to measured wind pressure, performing function fitting to obtain a fitted lift coefficient model and a fitted drag coefficient model at the different turbulence intensities, and selecting a corresponding fitted lift coefficient model and drag coefficient model according to a turbulence intensity on a wind turbine to be measured, to directly calculate a lift coefficient and a drag coefficient for the aerodynamic force of the airfoil.

The present invention discloses a large-scale model testing system of a floating offshore wind power generation device, and a method for manufacturing the large-scale model testing system. The large-scale model testing system comprises a floating wind power generation device model, model response measurement systems and environmental parameter measurement systems. The floating wind power generation device model comprises a floating foundation and a tower, wherein a wind turbine is connected to the top of the tower. A plurality of anchoring devices is connected to the side surface of the floating foundation. Each model response measurement system comprises an IMU unit, a wind turbine monitoring unit and an anchoring tension measurement unit. Each environmental parameter measurement system comprises a buoy-type wave height meter, a wind speed and direction meter and a flow velocity and direction meter.

The present invention discloses a large-scale model testing system of a floating offshore wind power generation device, and a method for manufacturing the large-scale model testing system. The large-scale model testing system comprises a floating wind power generation device model, model response measurement systems and environmental parameter measurement systems. The floating wind power generation device model comprises a floating foundation and a tower, wherein a wind turbine is connected to the top of the tower. A plurality of anchoring devices is connected to the side surface of the floating foundation. Each model response measurement system comprises an IMU unit, a wind turbine monitoring unit and an anchoring tension measurement unit. Each environmental parameter measurement system comprises a buoy-type wave height meter, a wind speed and direction meter and a flow velocity and direction meter.

Method for identifying slow transient variations and/or local spatial variations in vehicle related fluid dynamic conditions of a physical property in a set of data points. The method includes obtaining a first set of data points, calculating a temporal filtered value of the representation of the physical property for at least a portion of the first set of data points distributed over the total time period, combining at least a portion of the calculated temporal filtered values to obtain a second set of data points, and analysing in time sequence the second set of data points over at least a portion of the total time period.

Radiation curable compositions for additive fabrication processes, the components cured therefrom, and their use in particle image velocimetry testing methods are described and claimed herein. Such compositions include compounds which induce free-radical polymerization, optionally compounds which induce cationic polymerization, a filler constituent, and a light absorbing component, wherein the compositions are configured to possess certain absorbance values at wavelengths commonly utilized in particle image velocimetry testing. In another embodiment, the compositions include a fluoroantimony-modified compound. Such compositions may be used in particle imaging velocimetry testing methods, wherein the test object utilized is created via additive fabrication and is of a substantially homogeneous construction.

A wind tunnel sting comprising a support member and a wind tunnel sting damper. The support member having a first support-member end configured for coupling with a wind tunnel, and a second support-member end configured for coupling with a balance. The wind tunnel sting damper having a reactive member, and a viscoelastic member disposed between the reactive member and the support member wherein, the reactive member is sized relative to the support member so as to radially compress the viscoelastic member against the support member.

A wind tunnel sting comprising a support member and a wind tunnel sting damper. The support member having a first support-member end configured for coupling with a wind tunnel, and a second support-member end configured for coupling with a balance. The wind tunnel sting damper having a reactive member, and a viscoelastic member disposed between the reactive member and the support member wherein, the reactive member is sized relative to the support member so as to radially compress the viscoelastic member against the support member.

A wing model for static aeroelasticity wind tunnel test belongs to the technical field of aeroelasticity tests. In the wing model, the model steel joint and the spar frame are connected with the composite material skin. The piezometer wing ribs are arranged among the spar frame and the plurality of supporting wing ribs. The embedded piezometer tubes are arranged in the piezometer wing ribs, the lightweight filling foam is arranged among the spar frame and the plurality of supporting wing ribs. An outer surface of a frame segment formed by the lightweight filling foam, the plurality of supporting wing ribs, the piezometer wing ribs and the spar frame is covered with the composite material skin. The frame segment is assembled on the model steel joint to form the wing model for the static aeroelasticity wind tunnel test.

A wing model for static aeroelasticity wind tunnel test belongs to the technical field of aeroelasticity tests. In the wing model, the model steel joint and the spar frame are connected with the composite material skin. The piezometer wing ribs are arranged among the spar frame and the plurality of supporting wing ribs. The embedded piezometer tubes are arranged in the piezometer wing ribs, the lightweight filling foam is arranged among the spar frame and the plurality of supporting wing ribs. An outer surface of a frame segment formed by the lightweight filling foam, the plurality of supporting wing ribs, the piezometer wing ribs and the spar frame is covered with the composite material skin. The frame segment is assembled on the model steel joint to form the wing model for the static aeroelasticity wind tunnel test.

A flutter wind tunnel test model simulates a shape and vibration property of an aircraft part, for a flutter wind tunnel test of the aircraft part. The model at least partially has non-solid structure having branched clearances inside. A volume of a portion, other than the clearances, of the non-solid structure, per unit volume is defined by density. A method of producing a flutter wind tunnel test model simulating a shape and vibration property of an aircraft part, for a flutter wind tunnel test of the aircraft part, includes: shaping non-solid structure with a three-dimensional printer and composing at least a part of the flutter wind tunnel test model using the non-solid structure. The non-solid structure has branched clearances inside. A volume of a portion, other than the clearances, of the non-solid structure, per unit volume is defined by density.