China Aerodynamics Research Institute of Aeronautics

Shenyang, China

China Aerodynamics Research Institute of Aeronautics

Shenyang, China
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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.


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.


Yi B.,China Aerodynamics Research Institute of Aeronautics | Zeng K.,China Aerodynamics Research Institute of Aeronautics | Wang S.,China Aerodynamics Research Institute of Aeronautics
Kongqi Donglixue Xuebao/Acta Aerodynamica Sinica | Year: 2016

For the test of a flat-after-body flying wing aircraft model in high speed wind tunnel, the after-body has to be modified to satisfied the attachment of the balance. The deformation and the means of tail support may have some effect on the aerodynamic characteristics of the aircraft, and further affect the cruising efficiency, the trimming angle and the location of the aerodynamic center. On the other hand, there are no commonly used horizontal tail and vertical tail for a flying wing aircraft in order to reduce RCS, the interference of distorted after-body can not to be neglected compares to weak lateral controllability. With the help of CFD and test technique, the distorted after-body support interference has been obtained, in which rear sting is the main support and ventral strut an auxiliary one. The research indicates that the result of the wind tunnel test is accurate and reliable, the correction method can be adopted for the similar configuration model test. The methods of both numerical simulation and wind tunnel tests have been used to correct tail support interference of a flying wing model successfully. © 2016, Zhongguo Kongqi Dongli Yanjiu yu Fazhan Zhongxin. All right reserved.


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.


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.


Feng Q.,China Aerodynamics Research Institute of Aeronautics | Zhang Y.,China Aerodynamics Research Institute of Aeronautics | Cui X.-C.,China Aerodynamics Research Institute of Aeronautics
Shiyan Liuti Lixue/Journal of Experiments in Fluid Mechanics | Year: 2013

An experiment was conducted to investigate aerodynamic characteristics of flying wing aircraft with opened weapons bay by means of force and moment measurements. The results indicate that, for flying wing configuration aircraft, the increment of total vehicle drag was as much as 60%~110% when the weapons bay doors opened, and lift-drag ratio reduced by 34% at Ma=0.8. Conventional leading edge spoilers were used to disturb free shear layer of the weapons bay. Using the flow control method, additional drag of weapons bay can be reduced by 20% at most, and the lift-drag ratio increased by 12.6% at Ma=0.8.


Yu Y.-Z.,China Aerodynamics Research Institute of Aeronautics | Liu J.-F.,China Aerodynamics Research Institute of Aeronautics | Jiang Z.-Y.,China Aerodynamics Research Institute of Aeronautics | Chen B.,China Aerodynamics Research Institute of Aeronautics
Kongqi Donglixue Xuebao/Acta Aerodynamica Sinica | Year: 2011

In this paper, numerical simulation has been used to research the flow characteristics and mechanism of transport aircraft aft-body, vortex generators were used to control separated flows of aft-body, and it got an analysis of drag reduction mechanism by controlled, and also discussed the effect of different parameters on drag reduction. Calculation results show that: the drag of transport airplane aft-body is mainly caused by the flow separation of aft-body; vortex generators were fixed on the bottom of aft-body, and reached a certain drag reduction in the negative angle of attack. Size, circumferential distance and the forward or after location on the body of vortex generator have a certain influence with the drag reduction results.


Fang Y.,China Aerodynamics Research Institute of Aeronautics | Zhou Z.,China Aerodynamics Research Institute of Aeronautics | Zhang L.,China Aerodynamics Research Institute of Aeronautics
Shiyan Liuti Lixue/Journal of Experiments in Fluid Mechanics | Year: 2015

Based on the incompressible potential flows theory of low speed wind tunnel test, for the test of aircraft ground effect, a method is proposed to calculate and obtain the corresponding data for different floor heights of floor from the test data without the floor. The validity of the method is demonstrated by comparing the calculated results with the test data. Meanwhile, correcting the calculated results corresponding to existing test data with the floor can decrease the error of the data predicted by the method. ©, 2015, Shiyan Liuti Lixue/Journal of Experiments in Fluid Mechanics. All right reserved.


Feng Q.,China Aerodynamics Research Institute of Aeronautics | Cui X.,China Aerodynamics Research Institute of Aeronautics
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | Year: 2012

An experimental investigation is conducted in a high speed wind tunnel to suppress the acoustic resonance and additional drag of a weapons bay for flying wing configuration aircraft and to improve its store separation characteristics when its doors are opened. Conventional leading edge spoilers are used to disturb the weapons bay free shear layer. Detailed static-pressure and fluctuating-pressure measurements are obtained on the weapons bay walls to determine the effects on weapons bay flow characteristics. Forces and moments on the aircraft and the store model are measured to determine the effects of the flow control method on additional drag and store separation characteristics. The results indicate that for a flying wing configuration aircraft, the additional drag of the weapons bay accounts for as much as 60%-110% of the total vehicle drag. The amplitude of resonant tones is measured up to 185 dB. Very large pitching moment renders store release difficult, and it may cause the stores to rise back into the cavity and collide with the aircraft. Using the flow control method can reduce the amplitude of the weapons bay tones by 5-8 dB and can reduce additional drag up to 20%. Meanwhile, spoilers can enhance the characteristics of weapon departure from the weapons bay effectively.


Pan J.,China Aerodynamics Research Institute of Aeronautics | Zhang J.,China Aerodynamics Research Institute of Aeronautics | Cai Y.,China Aerodynamics Research Institute of Aeronautics | Xu M.,China Aerodynamics Research Institute of Aeronautics
Kongqi Donglixue Xuebao/Acta Aerodynamica Sinica | Year: 2016

Accurate dynamic derivative is particularly important with the development of modern high-maneuverability flying vehicles. The requirement of dynamic derivative wind-tunnel test technique is much stricter in precision and accuracy nowadays. High-speed dynamic derivative tests face more difficulties compared to low-speed ones due to small size of the model and high aerodynamic loads, small oscillation amplitude. According to the characteristics mentioned above, stress situation study during model oscillation, oscillation mechanism design and signal interference are analyzed and summarized in details, which are all applied on production test model in the wind tunnel. The results showed that the high-speed wind tunnel dynamic derivative repeatability increase to less than 10%. Through the research work done, the high-speed dynamic stability derivatives measurement technique has been improved. Also the developing trendy of the high-speed dynamic stability derivatives measurement test technique is briefly presented. © 2016, The Editorial Board of ACTA AERODYNAMICA SINICA. All right reserved.

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