Experiment technologies:

◆Aircraft Static Aerodynamic Performances Test
　　In order to meet the requirements for static aerodynamic and aviation performances in aircraft design process, AVIC Aerodynamics Research Institute（ARI）engaged in high-precision measurements and test technology researches. The evaluation technology of wind tunnel test data uncertainties as well as the step/continuous collecting methods have been in-depth studied. As a consequence of many years’ efforts, the attack of angles were expanded to cover the whole flight envelope and our wind tunnels have the abilities to measure the static aerodynamic characteristic and stability derivatives.

◆Aircraft Dynamic Aerodynamic Performances Test
　　As a main research filed of aerodynamic community, aircraft dynamic characteristics is one of our study focuses. Several dynamic test devices have been designed, such as a rotary balance test system, an angle vibrating system, a linear displacement oscillatory system, etc. AVIC ARI owns the capacities to measure dynamic parameters of test models in either low speed region or transonic region.

◆Engine Simulation Test
　　As the pioneer of the research on engine intake and exhaust synchronous simulation in China, AVIC ARI started this kind of study in 1982. From FL-2, FL-7 to FL-8, a unique series test system has been accomplished. Especially, the designs of ejectors were in China's first-level. Blowdown ratio of nozzle could arrive at 100%. Furthermore, China’s unique TPS calibration tank of which resistance cell measurement precision reaches 0.024% is in AVIC ARI.

◆Aircraft Maneuver Characteristic Test
　　In order to meet the requirements of aircraft’s maneuver characteristic research, several advanced devices have been designed, including high amplitude dynamic test device, dynamic integral test system and two-degree of freedom (pitch-roll) system. AVIC ARI has primarily abilities to serve the typical maneuver characteristic wind tunnel tests.

◆Inlet Performances Test
　　For many years in the past, AVIC ARI engaged in the research of inlet performances tests. Several mature test techniques and equipments have been established which focus on the dynamic and static inlet performance test. Simultaneously, one of our flowmeters with a high-precision (less than 0.3%) is the domestic biggest inlet flux measurement device, and it is also at international leading level.

◆High/Variable Reynolds Number Test
　　Researches on high/variable Reynolds number testing technique have been undertaken in both FL-9 low-speed pressurized wind tunnel and FL-2 pressurized three-sonic wind tunnel. Furthermore, based on these wind tunnels, an aeronautical high Reynolds number aerodynamic technique key laboratory has been set up. The highest Reynolds number of FL-9 wind tunnel is up to 22×106 (referenced distance is 1m), therefore this facility has abilities to serve the high Reynolds number test for taking off and landing configuration in aircraft flight envelope.

◆External Store Jettison and Separation Test
　　In order to meet the requirements of verifications for store jettison and separation characteristic, AVIC ARI systematically researched on technology of captive trajectory system (CTS). At the present time, two series of CTS test systems with small blockage have been designed and manufactured, and these systems are valuable to engineering applications.

◆Multi-balance Components and Hinge Moment Test
　　In order to satisfy the needs of aircraft design, AVIC ARI systematically researched on test technique of hinge moment in wind tunnel. By optimization of balance equipment and model mechanism, advanced test technique about hinge moment measurements, such as the measurement in aileron, horizontal rudder, and yaw rudder have been achieved.

◆OPS and PSP
　　AVIC ARI also engaged in researches on OPS and PSP technique. After several times tests, this technique is preliminarily available for engineering applications and takes the leading position in China.

◆Multi-Sheet Light Flow Visualization and Image Manipulation Technique
　　AVIC ARI has developed the multi-sheet light flow visualization technology based on the revolving mirror parallel multi-sheet light device and has resolved the technological issues of continuous barometric particle generation and multi-frame phase average of the dynamic flow visualization image manipulation and three-dimensional reconstruct of flow display image, besides, has actualized vortex flow vortex characteristics and vortex core accuracy display.

◆PIV Technique
　　AVIC ARI has studied the PIV technology in the large scale low speed wind tunnel, and formed the practical PIV flows visualization and measurement technology. The range of measuring speed is between 0 and 100 m/s, while the minimum spatial resolution is 0.1mm. This PIV technology has made the international leading position in large-scale wind tunnel. It could provide fast, accurate, complete and reliable data for the aircraft design and research on flow principle.
◆CFD Software Design and Development
　　In consideration of aeronautic CFD requirement, AVIC ARI has developed own aeronautic numerical simulation platforms which are named ENSMB and UNSMB. Both of the two platforms are based on parallel computational technique. Using structured and unstructured grid, the Euler and RANS equations have been solved on both of the platforms. Simultaneously, several grid generation codes have been also designed. The reliabilities of these platforms and codes have been validated in several standard cases. Furthermore, these platforms were preliminarily used in aeronautical engineering applications.

◆CFD engineering applications
　　In order to fulfill the demand of accuracy in wind tunnel tests and aerodynamic configuration design, AVIC ARI has expanded some CFD applications fields, such as support interference, wall interference, aeroelastic interference and aerodynamic optimization design. By combining with wind tunnel tests, substantial progresses have been achieved.

◆The Multi-Subject and Multi-Objective Optimization Design
　　According to the requirement of the multi-subject and multi-objective optimization design, the optimization method has been researched in AVIC ARI. The optimization for airfoil design based on gene algorithm, response surface methodology, hierarchical strategy, and Nash method have been developed. In the future, optimization for wing, wing body, and three-dimensional airplane configurations will be researched systematically.

◆Fixed-Wing Aircraft Configuration Research
　　AVIC ARI was engaged in fixed-wing aircraft aerodynamic configuration research for many years. During this period, several types of configurations as well as the performance of various conventional and unconventional rudders have been studied in detail. Consequently, abundant aerodynamic data and laws of stability and control have been gained which provide dependable basic information for aircraft designers.

◆Fan-wing Aircraft
　　Recently, by researching the layout design of Fan-wing Aircraft, AVIC-ARI has mastered its principle of flight and structural layout optimization of fan-wings. Furthermore, a prototypes has been designed and manufactured.
Theoretical Researches

◆Study on Complex Flow Mechanism (free-rolling and free-yawing tests)
　　To test the motions of free-rolling and free-yawing, AVIC-ARI researched the flow mechanism of aircraft at a high attack of angle, and has developed the test equipments which had been used to the wind tunnel tests including the time history measuring of free-rolling and free-yawing, flow visualization, load measuring of force-rolling, etc.

◆Synthetic Jet Flow
　　AVIC ARI has explored on the technology of active control on the flow of zero mass jet generator and has developed a piezoelectricity jet generator and a mechanism jet generator, besides, has studied the effect of the control on flow separation and the optimum design of the generator preliminarily.

◆Plasma Drag Decrease
　　AVIC ARI has explored on the mechanism of plasma drag decrease and has developed the one side discharge plasma generator independently, besides, has investigated on the plasma control of flow separation and drag decrease with the methods of CFD numerical simulation and the wind tunnel experiments.