一种高升力旋翼翼型静态高速风洞试验装置及方法
By improving the wall pressure strip structure, pressure guide pipe connection, and wake rake design, the problems of data fluctuation and Reynolds number mismatch in high-speed wind tunnel tests of rotor airfoils were solved, achieving high-precision wall pressure measurement and wake drag measurement, thus improving the accuracy and reliability of test data.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
- Filing Date
- 2026-05-18
- Publication Date
- 2026-07-17
AI Technical Summary
Existing high-speed wind tunnel tests for rotor airfoils suffer from problems such as large fluctuations in wall pressure measurement data, mismatch between experimental Reynolds number and real environment, and difficulty in balancing wake measurement resolution and interference.
The wall pressure strips and pressure guide pipes with a stepped hole structure, the moving wake rake and the wind tunnel pressure control system ensure accurate acquisition of wall pressure data, simulate the real flight Reynolds number environment, and achieve high-resolution, low-interference wake measurement through the moving wake rake.
It eliminates non-physical fluctuations in wall pressure measurement, enables accurate simulation of the Reynolds number in real flight at high Mach numbers, improves the resolution and overall correction accuracy of wake drag data, and enhances the accuracy and reliability of rotor airfoil aerodynamic data.
Smart Images
Figure CN122192695B_ABST