Test technology on unsteady characteristics of inlet flow during fighter plane maneuvers

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A test facility was developed in the Φ3.2m wind tunnel, which is driven by two moment electromotors and used to simulate inlet working conditions of the fighter during high maneuvers. The unsteady test method for research on the inlet flow characteristics was established. Based on results of the validating test, the inlet flow characteristics during maneuvers with rapidly changing angle of attack were studied. Some unsteady features, such as the circumferential distortion and turbulence, were obtained from the tests. All these results prove the feasibility of the test technology on studying the unsteady characteristics of the fighter plane inlet flow during maneuvers in the low speed wind tunnel. © 2017, Editorial Department of JOURNAL OF EXPERIMENTS IN FLUID MECHANICS. All right reserved.

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... Wu Chaojun and others developed a maneuvering inlet test device based on dual torque motor synchronous drive, simulated the rapid pitching and other maneuvering processes of the fighter and different working conditions of the inlet, and established the unsteady test method of the fighter inlet. The basic law of inlet performance change during a fast pitch maneuver of a fighter model is studied by means of the test [8]. Yang Yingkai conducted a wind tunnel test study on the dynamic characteristics of the bump inlet on both sides and explored the aerodynamic characteristics of the inlet within a certain angle of attack. ...
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Submerged inlet has been widely used in UAVs and cruise missiles due to its good stealth characteristics, but it also brings the disadvantage of poor aerodynamic characteristics. Especially in large maneuvering flight, the flow field near the fuselage has a strong unsteady effect, and the total pressure recovery coefficient and distortion characteristics have deteriorated sharply. In order to investigate the steady and transient aerodynamic characteristics of the submerged inlet in large maneuver flight and improve its maneuver envelope, a design scheme of a distributed submerged inlet for large maneuver flight is proposed in this paper. Taking a cruise missile as the research object, the steady and transient analysis of the conventional submerged inlet and the distributed submerged inlet is carried out using CFD numerical method. The results show that the distributed submerged inlet can significantly improve the inlet performance and enhance the sideslip limit of the submerged inlet during large sideslip maneuver flight. When the sideslip angle is 30°, compared with the conventional submerged inlet configuration, the outlet total pressure recovery coefficient of the distributed submerged inlet configuration is increased by 44.2%, and the total pressure distortion index is reduced by 66.3%.
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