FL⁃61结冰风洞翼型俯仰振荡机构研制

doi:10.7527/S1000-6893.2023.29296

Abstract

Abstract:

To study the icing characteristics of airfoil during the periodic variation of the angle of attack， an oscillating mechanism adapted to the FL-61 icing wind tunnel was developed. This mechanism enables the airfoil’s angle of attack to vary sinusoidally during icing tests. The mechanism is installed on the active side of the test section sidewall and the rotational speed of a servo motor is adjusted to achieve continuous adjustment of the airfoil’s pitching motion frequency. The amplitude of the airfoil’s motion can be modified by changing the mechanical eccentric wheel， and the average angle of attack can be adjusted by replacing the adapter. This design offers advantages such as the unidirectional rotation of the servo motor， lower demands on motor dynamics， and simplified control method. Through testing， the mechanism has demonstrated the angle control accuracy （≤3'），the maximum oscillation frequency （6 Hz）. The device has been successfully applied in the FL-61 icing wind tunnel， showing good repeatability and obtaining ice formation characteristics under various oscillation conditions， providing an experimental platform for further research on the icing characteristics of airfoils in pitching motion and oscillation.

Key words: icing, wind tunnel test, icing wind tunnel, oscillation, airfoil

CLC Number:

V216.8

Lingsong XU, Yuan WU, Dongyu ZHU, Fukun ZHANG, Yu LIU. A wing pitch oscillation mechanism for FL⁃61 icing wind tunnel[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(S2): 729296-729296.

Figures/Tables 18

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Table 1

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References 24

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工况	平均迎角/（°）	幅度/（°）	频率/Hz	总温/℃
1	3.5	0	0	-5
2	3.5	0	0	-5
3	3.5	±3	4	-5
4	3.5	0	0	-20
5	3.5	±3	4	-20
6	3.5	0	0	-10
7	3.5	±3	0.01	-10
8	3.5	±3	0.1	-10
9	3.5	±3	0.25	-10
10	3.5	±3	0.5	-10
11	3.5	±3	1	-10
12	3.5	±3	2	-10
13	3.5	±3	4	-10
14	3.5	±3	1	-10
15	-1.5	0	0	-10
16	-1.5	±6	4	-10

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A wing pitch oscillation mechanism for FL⁃61 icing wind tunnel

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