Testing Research Of Aerodynamics Performance Of Helicopter Rotor Model

In the ambient flight environment of helicopter, not only the complex aerodynamic characteristics exist, but also severe vibration problems emerge. For the presence of aeroelasticity effects, it's difficult to investigate such problems above. The helicopter aerodynamics and dynamics analysis and calculation software, which have been developed so far, is much less reliable than that of fixed-wing airplane, thus many important problems must be solved though full-scale flight tests. Consequently the lead time and risk of new type helicopter development get longer and higher. So for the design of new type helicopter and research of rotor aerodynamics, structure dynamics and aeroelastic stability, it's significantly important to carry on investigation of wind tunnel test techniques for helicopter model.The preparation works before test, contents of ground debug, method and procedure of ground hovering test and trimmed forward flight wind tunnel test, and techniques of test data acquisition and processing are introduced in this paper. Also the method of safety monitor is confirmed. Based on a certain rotor model, we obtained characteristic test data of hovering and forward flight. And analysis of the test results shows: test data acquired was reasonable and reliable.The loads measurement method of pitch pole and blade bending are introduced in the paper, together with the test results presented, all above provided main basis for rotor blade hinge moment obtaining and blade durability pre estimating. By the means of different rotor tip model performance comparison tests in states of hovering and forward flight, we got some significant conclusions, therefore offered test basis for the rotor designing in the process of helicopter development. Also though the force and surface pressure measurements tests performed by the use of BO-105 rotor model and Z9 fuselage model, we obtained some general rules of rotor-fuselage aerodynamic interaction, and explored the interaction mechanism preliminarily. The quantitative results are demonstrated in the paper as well.By the use ofΦ4m rotor-fuselage model combination test stand, we conducted research of rotor model aerodynamic test works in 8m><6m wind tunnel, and got well practice of the techniques about ground hovering test, trimmed forward flight test , pitch pole loads measurement, blade bending moment measurement, also had well understand of influence of rotor tip on the rotor aerodynamics, thus we can provided important test basis for the rotor designing in the process of helicopter development.