Rotor wind tunnel test method based on distributed jet active flow control

By employing a systematic rotor wind tunnel testing method, the lack of rotor testing methods for distributed jet active flow control was resolved, enabling effective research on rotor aerodynamic performance and improvement of flight speed.

CN121898732APending Publication Date: 2026-04-21CHINA AVIATION IND CORP HARBIN AERODYNAMICS RESEARCH INSTITUTE
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Patent Information

Application Number
CN202610355925.0
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2026-03-23
Publication Date
2026-04-21

AI Technical Summary

Technical Problem

Currently, there is no systematic and effective method for rotor wind tunnel testing based on distributed jet active flow control, which makes it impossible to effectively study the aerodynamic characteristics of rotors and improve flight speed.

Method used

By conducting dynamic characteristic tests on the rotor test bench, calibrating the rotor control matrix, adjusting the dynamic balance and conicity, and combining the distributed jet rotor model to carry out hovering and forward flight tests in the wind tunnel, the test data were collected, processed, and the aerodynamic performance was analyzed.

Benefits of technology

A systematic standard procedure for rotor wind tunnel testing was established, which improved the safety and reliability of the test, reduced equipment wear and tear and time costs, shortened the R&D cycle, and provided reliable methodological guidance from the laboratory to engineering applications.

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Abstract

The invention discloses a distributed jet active flow control-based rotor wind tunnel test method, which belongs to the technical field of aviation aerodynamic wind tunnel tests, and comprises the steps of rotor test bed dynamic characteristic test, manipulation matrix calibration, preposed preparation of rotor model dynamic balance and common taper adjustment, and dynamic balance and common taper adjustment. And then hovering and forward flight wind tunnel tests of distributed jet active flow control are carried out in sequence, test data are collected and processed, and the aerodynamic performance of the rotor wing under the condition that jet control exists or not is compared and analyzed. According to the invention, the industrial blank of the lack of a distributed jet active flow control rotor wind tunnel test method is filled, and key technical support is provided for theoretical research, technical optimization and engineering application of the rotor distributed jet active flow control method.
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