A method for determining the aerodynamic moment of resistance M.sub.aero-EM of a wheel arranged on an axis, by measuring the value of the mechanical power P.sub.m to be applied to the wheel in order to maintain it in rotation at a constant speed ω, the said wheel being equipped with a rotational-drive means and with a device for picking off and/or recording the numerical values of the said mechanical power and those of the rotational speed. The wheel is protected by a removable cap and is subjected to a flow of air.

A method for determining the aerodynamic moment of resistance M.sub.aero-EM of a wheel arranged on an axis, by measuring the value of the mechanical power P.sub.m to be applied to the wheel in order to maintain it in rotation at a constant speed ω, the said wheel being equipped with a rotational-drive means and with a device for picking off and/or recording the numerical values of the said mechanical power and those of the rotational speed. The wheel is protected by a removable cap and is subjected to a flow of air.

Pressure measurement apparatus, assemblies and methods are described. According to one aspect, a pressure sensor assembly includes a substrate, a first adhesive member adhered to the substrate, a sensor support adhered to the first adhesive member, a second adhesive member adhered to the sensor support, and a pressure sensor adhered to the second adhesive member and aligned with apertures of the substrate, first adhesive member, and second adhesive member, and the pressure sensor is configured to vary an output signal as a result of changes in pressure of a received air stream, and the output signal is indicative of the changes in pressure of the air stream.

A method for predicting if a flow over a smooth ramp surface will separate from the ramp surface, wherein the ramp surface has a slope that is everywhere non-positive along the length of the ramp surface relative to the flow at the inflow end of the ramp surface includes i) dividing the height of the ramp surface by the length of the ramp surface to determine a height-to-length ratio of the ramp surface, ii) identifying a maximum slope magnitude of the ramp surface, iii) calculating a maximum normalized slope by dividing the maximum slope magnitude of the ramp surface by the height-to-length ratio of the ramp surface, and calculating a critical ramp slope as a linear function of the height-to-length ratio of the ramp surface. If the maximum normalized slope is greater than the critical ramp slope, the method predicts the turbulent boundary layer will separate from the ramp surface.

An electrode performance evaluation system and an electrode performance evaluation method is disclosed. The method includes acquiring impedance measurement data for different frequencies by applying an alternating current signal to an electrode assembly including an electrode which is immersed in an electrolyte solution, calculating impedance calculation data for different frequencies while changing the frequency of an impedance equation corresponding to a circuit model of the electrode assembly, calculating the resistance value of ion bulk resistance in the electrolyte solution using the ion conductivity of the electrolyte solution, the area of the electrode and the thickness and porosity of an active material layer of the electrode, and determining effective tortuosity as a factor of the electrode performance based on the impedance measurement data for different frequencies, the impedance calculation data for different frequencies and the resistance value of the ion bulk resistance.

A method for testing water droplet shedding ability of a surface of an aircraft wing includes: blowing air toward a surface of a cylindrical member in an airflow direction perpendicular to an axial direction of the cylindrical member, the cylindrical member simulating the wing and having water-related surface characteristics that differ across a predetermined boundary position in a circumferential direction; supplying a water droplet to a portion of the surface of the cylindrical member on a leading edge side with respect to a flow of the air; and capturing an image of the water droplet that moves on the surface of the cylindrical member across the boundary position due to the flow of the air.

A method for testing water droplet shedding ability of a surface of an aircraft wing includes: blowing air toward a surface of a cylindrical member in an airflow direction perpendicular to an axial direction of the cylindrical member, the cylindrical member simulating the wing and having water-related surface characteristics that differ across a predetermined boundary position in a circumferential direction; supplying a water droplet to a portion of the surface of the cylindrical member on a leading edge side with respect to a flow of the air; and capturing an image of the water droplet that moves on the surface of the cylindrical member across the boundary position due to the flow of the air.

In one aspect, a transducer body includes a support having clevis halves. The sensor body includes a generally rigid peripheral member disposed about a spaced-apart central hub joined to each of the clevis halves. At least three flexure components couple the peripheral member to the hub. The flexure components are spaced-apart from each other at generally equal angle intervals about the hub; the sensor body further including a flexure assembly for some flexure components joining the flexure component to at least one of the hub and the peripheral member, the flexure assembly being compliant for forces in a radial direction from the hub to the peripheral member. Each flexure assembly is configured such that forces transferred concentrate strain at a midpoint along the length of each corresponding flexure component.

An assembly quality detection device and a method for a wind screen cleaning system based on streamline pattern, includes a main body of a test bench and a detection system. The main body of the test bench includes a test bench rack and a cleaning centrifugal fan; the inside of the test bench rack is provided with a cleaning space. The detection system includes a smoke generation and transmission device, a two-degree-of-freedom smoke fixed-point release mechanism, a high-speed image acquisition system and a control system. A fixed base is installed on the upper end of the outlet of the cleaning centrifugal fan, a linear moving guide rail device is installed on the fixed base, the linear moving guide rail device is equipped with a moving slider, the moving slider is installed with a rotating mechanism, the rotating mechanism output end is provided with a smoke releasing duct, the smoke releasing duct is communicated with the smoke generation and transmission device. The detection device and method can test the manufacturing and assembly quality of the cleaning system of the combine harvester by combining the characteristics of wind tunnel streamline pattern with image processing and corresponding mathematical operation.

A parameter similarity method for test simulation conditions of an aerodynamic heating environment is disclosed. With respect to the requirement that the adiabatic wall enthalpy and the cold-wall heat flux are equal in the simulation test of the aerodynamic heating environment, a method that can ensure the similarity of ground test parameters and flight parameters without the equal adiabatic wall enthalpy is proposed, and solves the problems of relying on the equal adiabatic wall enthalpy and making it difficult to accurately simulate the real aerodynamic heating environment in the current test simulation method, and provides guarantee for heat transfer and ablation test research of thermal protection/insulation material under the high temperature aerodynamic heating environment. The test conditions are not affected by the value of the adiabatic wall enthalpy. According to the method, most test devices can simulate the aerodynamic heating environment with high enthalpy.