Experimental Study on the Flow Characteristics of a Slender Body of Revolution in the Leeward Region under High-speed Condition

doi:10.12382/bgxb.2022.0688

Abstract

Abstract:

The transition and flow separation dominated by vorticity will occur, which have a significant impact on the maneuverability and control ability of missile, when a missile launches an all-aspect attack. The particle image velocimetry (PIV) and fluorescent oil flow visualization experiments are carried out in the FD-12 wind tunnel for a slender body in order to explore the influences of angle of attack and Mach number on the flow pattern in the leeward region of slender body.The characteristics of the flow field in the leeward region of slender body were obtained at the angles of attack α from 0° from180° with Ma=0.4/0.6/0.8. The results show that the flow in the leeward region of the model changes from attached flow to separation flow, and the separation vortex vary from symmetry to asymmetry when the angle of attack is <90°. The unsteady vortex shedding phenomenon exists in the leeward region and the time-averaged flow field has an obvious asymmetry characteristic at 100° and 120° angles of attack. The separation zone of windward face begins to appear asymmetric offset for α=150°. The lower boundary of initial separation zone crosses the end face of the model, forming a separation line in the rear of the model. When the angle of attack changes to 180°, there is an obvious ring-shaped separation zone and re-attachment zone at the upwind face and no obvious separation zone at the rear of the model. The results indicate that the flow field presents complex unsteady and nonlinear flow states due to the influence of bottom. In addition, the increase of the Mach not only enlarge the influence range of separation vortex, but also promote the position of separation vortex at the same angle of attack.

Key words: slender body, high angle of attack, particle image velocimetry, flow separation, vortex

CLC Number:

TJ590

LI Xiaohui, WANG Hongwei, XIONG Hongliang, SHI Weilong, REN Shaojie, HUANG Zhan. Experimental Study on the Flow Characteristics of a Slender Body of Revolution in the Leeward Region under High-speed Condition[J]. Acta Armamentarii, 2024, 45(3): 818-827.

Figures/Tables 23

Fig.1 Experimental model

Fig.2 Model installation(left: model suits; right: model reversal)

Table 1 Model preset angle of attack

预偏攻角/(°)	可实现攻角状态/(°)	模型部件更换
15	0~40	正装
75	60~100	正装
75	80~120	反装
15	140~180	反装

Table 2 Experimental conditions

Ma	攻角α/(°)	z/mm	试验手段
0.6	0	6.83D	PIV
0.4	30	6.83D	PIV
0.6	30	6.83D	PIV
0.8	30	6.83D	PIV
0.6	60	6.17D	PIV
0.4	80	6.17D	PIV
0.6	80	6.17D	PIV
0.8	80	6.17D	PIV
0.6	100	4D	PIV
0.6	120	4D	PIV
0.6	150	4D	PIV
0.6	180	4D	PIV
0.6	100		油流
0.6	120		油流
0.6	150		油流
0.6	180		油流

Fig.3 Camera built-in scheme

Fig.4 Experimental layout of oil film

Fig.5 Particle image and velocity flow distribution (left: particle image; right: velocity distribution)

Fig.6 Particle image and velocity flow distribution (left: particle image; right:velocity distribution)

Fig.7 Particle image and velocity flow distribution (left: particle image; right: velocity distribution)

Fig.8 Spatial flow structure for Ma=0.4(left: particle image; middle:instantaneous velocity distribution; right : time-averaged velocity distribution)

Fig.9 Spatial flow structure for Ma=0.6(left: particle image; middle:instantaneous velocity distribution; right: time-averaged velocity distribution)

Fig.10 Spatial flow structure for Ma=0.8(left: particle image; middle:instantaneous velocity distribution; right: time-average velocity distribution)

Fig.11 Time-averaged vorticity distribution diagram(left:Ma=0.4;middle:Ma=0.6;right:Ma=0.8;α=30°)

Fig.12 Diagram of leeward vorticity variation(α=30°)

Fig.13 Vertical distance between vortex core and the center of model section vs. Mach number(α=30°)

Fig.14 Horizontal distance of vortex core vs. Mach number(α=30°)

Fig.15 Instantaneous vorticity distribution diagram(upper:Ma=0.4;middle:Ma=0.6;below:Ma=0.8;α=80°)

Fig.16 Separation vortex vs. angle of attack(Ma=0.6)

Fig.17 Flow pattern of model

Fig.18 Calculation method of separation angle

Fig.19 Separation position(the numbers are pixel length)

Table 3 Calculated results of separation angle

α/(°)	z/D
α/(°)	1	2	3	4	5	6
100	101.31	101.11	103.57	104.62	101.58	102.16
120	106.45	105.11	109.90	109.32	106.05	106.95

Fig.20 Change of separation angle along the flow direction

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