砂纸冰对民机平尾气动特性的影响

doi:10.7527/S1000-6893.2023.28657

Abstract

Abstract:

Icing on the horizontal tail seriously affects the longitudinal controllability and stability of aircraft. To study the effect of roughness ice on the aerodynamic performance of the horizontal tail， we conduct a force test in a low-speed pressured wind tunnel using two horizontal tail models designed based on a civil aircraft horizontal tail， analyze the effect laws of the ice roughness， the horizontal tail Reynold number and the horn ice roughness on the horizontal tail aerodynamic performance， and summarize the scaling method of the roughness ice used in the wind tunnel. The results show that increase in ice roughness will gradually reduce the horizontal tail aerodynamic performance， and the maximal lift coefficient will decrease by 0.3-0.4 with the ice roughness relative height within 0.2×10^-3 to 0.6×10^-3 under flight Reynolds number compared to the clean tail； the influence of Reynolds number on the horizontal tail aerodynamic performance with roughness exceeds that on the horizontal tail with horn ice， though is much smaller than that on the clean horizontal tail， and the maximal lift coefficient will increase by approximately 0.02-0.04 when the Reynolds number of the horizontal tail with roughness ice increases from 3.29×10⁶ to 13.1×10⁶； the change in the surface roughness of the horn ice has less influence on the aerodynamic performance of the horizontal tail， and the lift loss caused by the roughness is much smaller than that brought by the horn ice itself； when the height of roughness ice significantly exceeds the thickness of the local boundary layer， the roughness ice could be directly scaled according to the geometric scaling of the model， and when the height of roughness ice is smaller than the thickness of the local boundary layer， the influence of roughness ice obtained through geometric scaling on the horizontal tail is relatively small. The roughness ice scaling method based on the boundary layer thickness is proposed， and the applicability of this method needs further verification.

Key words: roughness ice, horizontal tail, wind tunnel test, aerodynamic performance, roughness, Reynolds number, boundary layer

CLC Number:

V211.74

Haixing LI, Feng ZHOU, Wei YAN, Feng BAI, Keliang ZHAO. Effects of roughness ice on aerodynamic performance of civil aircraft horizontal tail[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(2): 128657.

Figures/Tables 29

Fig.1

Table 1

Table 2

Fig.2

Fig.3

Fig.4

Table 3

Test content

车次	模型比例	试验雷诺数/ $106$	砂纸冰目数	备注
1	1∶4	3.29	无
2	1∶4	3.29	40#
3	1∶4	3.29	80#
4	1∶4	3.29	120#
5	1∶4	13.10	无
6	1∶4	13.10	40#
7	1∶4	13.10	80#
8	1∶4	13.10	120#
9	1∶4	6.58	80#
10	1∶4	9.87	80#
11	1∶4	3.29	无	带角冰
12	1∶4	6.58	无	带角冰
13	1∶4	9.87	无	带角冰
14	1∶4	13.10	无	带角冰
15	1∶4	3.29	40#	带角冰
16	1∶4	3.29	80#	带角冰
17	1∶4	3.29	无	丝线
18	1∶4	3.29	无	带角冰+丝线
19	1∶11	1.20	无
20	1∶11	1.20	80#
21	1∶11	2.40	80#
22	1∶11	3.29	无
23	1∶11	3.29	80#
24	1∶11	3.29	100#
25	1∶11	3.29	240#
26	1∶11	3.29	320#

Table 3

Table 4

Measurement accuracy of balances under different conditions

模型比例	Re/ $106$	$Δ L$ /N	$Δ M$ /（N·m）	$Δ C L$	$Δ C m$
1∶4	13.10	20.00	8.80	0.001 6	0.001 0
1∶4	9.87	20.00	8.80	0.002 1	0.001 4
1∶4	6.58	20.00	8.80	0.003 2	0.002 0
1∶4	3.29	20.00	8.80	0.006 4	0.004 1
1∶11	3.29	2.00	0.54	0.001 6	0.001 7
1∶11	2.40	2.00	0.54	0.002 4	0.002 6
1∶11	1.20	2.00	0.54	0.004 8	0.005 2

Table 4

Fig.5

Table 5

Repeatability error of test

测量项目	$σ C L$	$σ C m$
本试验重复性	0.001 1	0.000 5
国家军用标准要求^［33］	0.004 0	0.001 2

Table 5

Fig.6

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Fig.15

Fig.16

Fig.17

Table 6

Fig.18

Fig.19

Table 7

Difference contrast of maximal lift coefficient， stall angle， inflection moment and inflection moment angle between 1∶4 and 1∶11 scale horizontal tail model without ice， or with roughness ice

h/MAC	$Δ C L, m a x$	$α s t a l l$ /（°）	$Δ C m, m i$	$Δ α m i$ /（°）
0.614 7	-0.012 6	-0.74	0.005 5	-0.84
0.260 5	-0.022 8	-0.67	0.015 3	-2.87
0.181 5	-0.022 6	-0.74	0.016 6	-5.52
0.001 2	0.015 9	0.35	-0.002 1	0.40

Table 7

Fig.20

Fig.21

Fig.22

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天平六分量	设计载荷	测量精度/% F.S.	模型六分量
Y/N	12 000	0.05	侧向力
X/N	10 000	0.05	阻力
Z/N	40 000	0.05	升力
M_y /（N·m）	8 000	0.11	俯仰力矩
M_x /（N·m）	40 000	0.03	滚转力矩
M_z /（N·m）	8 000	0.11	偏航力矩

天平六分量	设计载荷	测量精度/% F.S.	模型六分量
Y/N	8 000	0.04	侧向力
X/N	2 000	0.09	阻力
Z/N	5 000	0.04	升力
M_y /（N·m）	600	0.09	俯仰力矩
M_x /（N·m）	700	0.10	滚转力矩
M_z /（N·m）	1 200	0.03	偏航力矩

1∶4比例模型砂纸颗粒目数	1∶11比例模型砂纸颗粒目数	模型缩比值	颗粒缩比值
40#	100#	2.75	2.80
80#	240#	2.75	3.02
120#	320#	2.75	2.82
40#	80#	2.75	2.36

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Effects of roughness ice on aerodynamic performance of civil aircraft horizontal tail

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