A Subsonic Wind Tunnel Compressible Fluid Disturbance Modal Measurement Results Calculation Method
A technology for measuring results and compressing fluid, which is applied in the field of subsonic wind tunnel compressible fluid disturbance modal measurement results calculation, and can solve the problems of inability to accurately quantify the accuracy of test results
Active Publication Date: 2022-04-15
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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Problems solved by technology
At present, the compressible velocity domain of the subsonic wind tunnel plays an important role in the aerodynamic evaluation and refined design of the aerodynamic shape of many advanced large aircraft such as passenger aircraft, military transport aircraft, long-range strategic bombers, early warning aircraft, and tankers. The free-flow disturbance mode of the free flow has not been quantitatively evaluated, resulting in the inability to accurately quantify the accuracy of the test results
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Embodiment 1
[0086] The method for solving the measurement result of the disturbance mode of the compressible fluid in the subsonic wind tunnel in this embodiment is specifically described by the measurement test of the disturbance mode in the probe calibration wind tunnel.
[0087] The subsonic wind tunnel compressible fluid disturbance modal measurement result solution method of the present invention comprises the following steps:
[0088] a. Install the one-dimensional hot wire probe on the support rod, fix the support rod on the clamping mechanism, and install the entire clamping mechanism in the probe calibration wind tunnel test section;
[0089] b. Turn on the probe to calibrate the wind tunnel, and use the hot wire anemometer to measure the flow field pulsation under the incoming flow Mach number M=0.330, 0.420, 0.525, 0.627, 0.719 to obtain the mass flow pulsation total temperature fluctuation Cross-correlation between mass flow pulsation and total temperature pulsation The r...
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The invention discloses a subsonic wind tunnel compressible fluid disturbance mode measurement result calculation method. The method includes the following steps: (1) data acquisition preparation; (2) using a hot wire anemometer to measure flow field fluctuations in the test section of a subsonic wind tunnel to obtain mass flow fluctuations, total temperature fluctuations, and cross-correlation between mass flow fluctuations and total temperature fluctuations (3) Under the premise that the entropy mode is 0, derive and solve the acoustic mode and vortex mode; (4) derive and solve the basic physical quantities of the flow field, the acoustic mode and the vortex mode components. This method obtains the specific expressions of the disturbance mode in the compressible fluid in the subsonic wind tunnel and the basic physical quantities of the flow field, the acoustic mode and the vortex mode components, and uses the measurement results of the hot wire anemometer to solve the acoustic mode and vortex mode components of the flow field. The vortex mode, as well as the acoustic mode and vortex mode components of the basic physical quantities of the flow field, provide a feasible method for the analysis of the disturbance mode of the compressible fluid in the subsonic wind tunnel, and provide a technology for the flow field quality evaluation of the new wind tunnel support.
Description
technical field [0001] The invention belongs to the field of experimental aerodynamics, and in particular relates to a method for solving the measurement result of a subsonic wind tunnel compressible fluid disturbance mode. Background technique [0002] As we all know, the core flow area of the wind tunnel test section is the area with the best flow field quality in the wind tunnel after being rectified by the rectification device, but despite this, the free flow entering the wind tunnel test section still has unsteady characteristics. Free flow disturbance will affect the accuracy of wind tunnel test results, resulting in errors in wind tunnel test results. For aircraft design, errors in wind tunnel test results mean that there are design errors in aerodynamic parameters such as lift and drag coefficients, which in turn will lead to There is an estimation error in the load capacity of the aircraft, which seriously restricts the economy and safety of the aircraft. Therefo...
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IPC IPC(8): G01M9/08G01M9/06
CPCG01M9/08G01M9/065
Inventor 杜钰锋林俊王勋年
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT