Add: No.2, Yiman Street, Nangang District, Harbin, Heilongjiang Province, China
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Add: No.1, Yangshan Road, Huanggu District, Shenyang, Liaoning Province, China
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AVIC ARI specializes in high/low speed wind tunnel unsteady aerodynamics testing technologies, which has won a good reputation among the domestic customers for years, and provided reliable unsteady aerodynamic data and technical support for the design and manufacture of most aircraft projects in our country.
High/Low Speed Wind Tunnel Dynamic Derivatives Measurement Test
Low speed wind tunnels are equipped with low speed dynamic derivatives measurement testing devices with five motion modes( roll, yaw, pitch, heave, side translation), which is suitable for 1m-scale model wind tunnel test, and can measure combined dynamic derivatives and plunging derivatives, and can get direct damping derivatives, cross derivatives and coupling cross derivatives.
High speed wind tunnels are equipped with high speed dynamic derivatives testing devices with three motion modes( roll, yaw, pitch), which is suitable for 0.6m-scale model wind tunnel test, with the test conditions of Mach number range of 0.4-1.5, angle of attack range of -7°~24°, maximum oscillation frequency of 12Hz.
Low Speed Wind Tunnel Rotary Balance Test
AVICARI FL-8 and FL-51 wind tunnels are equipped with rotary balance testing system, which is suitable for 1m-scale model test having the model continuous rotating around velocity vector axis, aiming to get model aerodynamic characteristics while rotating around velocity vector axis. The range of angle of attack is -90°~90°, range of sideslip angels is -40°~40°, maximum rotation speed of main axis is 240rpm, and the wind speed range is 20m/s~45m/s.
High/Low Speed Wind Tunnel
Low speed wind tunnels are equipped with two degrees of freedom large amplitude oscillation testing system, which is driven by coupling of electrical/hydraulic motor, and suitable for 1m-scale model test. This system adopts rear support and can carry out three types of single degree of freedom large amplitude oscillation test(roll, yaw, pitch), two types of two degrees of freedom coupling oscillation test(roll/yaw coupling, roll/pitch coupling) and typical maneuver simulation test. Dynamic stability derivatives are obtained when small amplitude oscillation is produced by system. This system obviously offers advantages to special configuration models due to the reason that the three kinds of angle oscillations tests are tail-supported.
High speed wind tunnels are equipped with high speed two degrees of freedom large amplitude oscillation testing system, which is suitable for 0.6m-scale model test. This system can be used to carry out three types of single degree of freedom large amplitude oscillation tests and roll/pitch coupling motion test, with the oscillation amplitude of 20°~60°and the maximum frequency of 2Hz as well as test Mach number range of 0.4~0.9.
Low Speed Wind Tunnel Rotary Balance Test
Oscillation testing system under rotating flowfield is equipped. This system can achieve single degree of freedom (roll, yaw, pitch) oscillation movement during continuous rotating around velocity vector axis, and be used to obtain unsteady aerodynamic characteristics(for large amplitude) under rotating flowfield or dynamic stability derivatives(for small amplitude) under rotating flowfield, providing test data for spin prediction and spin recovering.
Low Speed Wind Tunnel Typical Maneuver Simulation Test
AVICARI has developed typical maneuver simulation test technology based on large amplitude oscillation test devices in FL-8 and FL-5 wind tunnels, which is used to obtain aerodynamic characteristics variation with time during aircraft maneuver flight, providing effective test method for advanced aircraft strategic maneuver aerodynamic validation as well as unsteady aerodynamic mathematical model validation.
High Speed Wind Tunnel Free-Roll Test
Free-roll test device has been established in AVICARI FL-3 wind tunnel, which can be used to research transverse non-instructed movement characteristics of aircraft having transonic sudden wing stall phenomenon, such as phenomena of heavy wing, wing drop and wing rock usually occurred during transonic maneuver flight, specifiially for aircrafts with sawtooth leading edge and folding wing aircraft. Angle of attack limit for abrupt wing stall is predicted using wind tunnel test, and certain measures are taken to avoid this aircraft non-instructed movement. Test Mach number range is 0.8~1.2, and test angle of attack range is -10°~30°