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Gao J.-J.,Beihang University | Jiao R.-S.,China Aerodynamics Research Institute of Aeronautics
Shiyan Liuti Lixue/Journal of Experiments in Fluid Mechanics | Year: 2011

To enhance the precision and accuracy of wind tunnel test of aircraft with large aspect ratio and flying wing, mounting forks (three-point-support) system had been developed in FL-8 low speed wind tunnel of CARIA. The test results of supports with two spatial shapes and two cross section shapes show that the mounting forks improved the rigidity of the whole test system, hence increased the test's precision, and the shape of support distinctly influenced the lateral test results, and subtly designed supports near the model are benefit to enhance the accuracy of wind tunnel test. Source


Yu J.,China Aerodynamics Research Institute of Aeronautics
Proceedings of 2010 Asia-Pacific International Symposium on Aerospace Technology, APISAT 2010 | Year: 2010

The generalized non-conservative system's generalized quasi-variational principle has great potential for analytical and approximate solutions for problems in science and engineering. The research on it is a very important research field that involves multiple disciplines. In the paper, considering the influences of damping forces and fellow forces and indicating basic equations of generalized non-conservative elasto-dynamics, according to the corresponding relations between generalized forces and generalized displacements, the basic equations of non-conservative elasto-dynamics were convoi-multiplied by corresponding virtual quantities, integrated and then added algebraically, we established generalized quasi-variational principles with two kinds of variables of generalized non-conservative elasto-dynamics by dint of the variational integral method. A example of aeroelasticity was solved by applying generalized quasi-complementary energy principles with two kinds of variables. Source


Yu J.,China Aerodynamics Research Institute of Aeronautics | Niu Z.,China Aerodynamics Research Institute of Aeronautics | Liang H.,PLA Air Force Aviation University | Guan J.,China Aerodynamics Research Institute of Aeronautics | Hu Q.,China Aerodynamics Research Institute of Aeronautics
Kongqi Donglixue Xuebao/Acta Aerodynamica Sinica | Year: 2015

Under the condition of wind speed of 30 m/s or 40 m/s, the effect of the parameter of the voltage and the number of actuated electrode couples as well as the position of the plasma aerodynamic actuation on the lift enhancement and drag reduction of a flying wing are investigated by means of force-balance tests in the wind tunnel after the nanosecond pulse die-lectric barrier discharge plasma actuator was installed. The force test results show that, compared with the voltage and the number of actuated electrode couples, the position of the plasma aerodynamic actuation determines flow control effect mainly. Compared with other control position, plasma inhibites model's leading edge vortices seperation obvious. Plasma actuator injectes energy to the boundary layer of fluid so the surface flow separation is delayed to larger angle of attack for the flying wing, the maximum lift coefficient and stall angle are also efficiently increased, and drag coefficient is reduced at the same time. Under certain test conditions, the maximum lift coefficient increases 13.2% from 0.97 to 1.1, stall angle increases 4° from 17.4° to 21.4° and drag coefficient reduces 24.6%, and the more energy the plasma actuator is increased, the more obvious effect the plasma actuator will generate. © 2015, Editorial Office of ACTA AERODYNAMICA SINICA. All right reserved. Source


Gao J.-J.,Beihang University | Liu C.-M.,China Aerodynamics Research Institute of Aeronautics | Bu C.,China Aerodynamics Research Institute of Aeronautics
Shiyan Liuti Lixue/Journal of Experiments in Fluid Mechanics | Year: 2012

This paper introduced the research of rotary balance test support interference in FL-8 low speed wind tunnel, including the test method, equipment and results. To realize the function of support and angle variation, an angle variation rod was designed. Test results showed that the support interference of the longitudinal and lateral aerodynamic forces was different, the influence of support interference was irrelative to the rotational direction in the longitudinal results, and it was opposite with different rotational direction in the lateral results. The results after support interference correction of dorsal and rear sting support were close to each other, which indicated that the correction was reasonable, and the accuracy of the test results was improved. Source


Shang J.-K.,China Aerodynamics Research Institute of Aeronautics | Ma X.-G.,China Aerodynamics Research Institute of Aeronautics
Shiyan Liuti Lixue/Journal of Experiments in Fluid Mechanics | Year: 2010

In this paper, a PSP image processing method combining image median filter and reference points is presented. This method uses hollow median filter to restore light intensity ratio at pressure taps in light intensity images and to obtain a relation between Cp values at reference points measured by conventional pressure measurement and light intensity ratio of PSP images, thus Cp values on the whole test model surface are acquired. This method indicates the effects of some factors brought by wind tunnel testing on testing results. PSP test images are processed using MATLAB software with a comparison of Cp values acquired by PSP method and conventional pressure measurement technique. Results show that Cp alues acquired by PSP method are consistent with those conventional Cp values. This method is a new PSP image processing method with a promising development potential and application value. Source

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