网格对高超声速钝头体表面热流数值模拟结果的影响

doi:10.7527/S1000-6893.2022.26710

Abstract

Abstract:

Accurate prediction of aerothermal heating load over hypersonic blunt bodies is of great significance to the design of hypersonic vehicle thermal protection， while grid metric affects the prediction accuracy of aircraft surface heating load. By theoretical analysis and numerical simulation， a grid generation method is proposed according to the cell Reynolds number and freestream Reynolds number， respectively， based on the wall parameters and characteristic length of blunt bodies， and the reference value range of the cell Reynolds number based on wall parameters is also provided. The proposed grid generation method is then applied to the simulation of hypersonic aeroheating computations over semi-cylinders and semi-spheres under different incoming flow conditions. The results show that the proposed grid generation method and the suggested range of the cell Reynolds number based on wall parameters can satisfy the precision requirement of thermal environment simulation over hypersonic blunt bodies， facilitate the rational distribution of grids， and simultaneously improve the efficiency of numerical calculations.

Key words: hypersonic flow, aerothermal heating, blunt body, error analysis, grid metric

CLC Number:

V211.5

Chongli MA, Jingyuan LIU. Effect of grid strategy on numerical simulation results of aerothermal heating loads over hypersonic blunt bodies[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(5): 126710-126710.

Figures/Tables 14

Fig. 1

Fig. 2

Fig. 3

Fig. 4

Fig. 5

Fig. 6

Fig. 7

Fig. 8

Fig. 9

Fig. 10

Fig. 11

Table 1

Collections of grid scales for different numerical cases

来流外形	$M a ∞$	$R e$	D/m	$λ w$	$Δ n w, m a x$ /m	$R e c e l l, w, m a x$	$Δ x m a x$ /m	$R e$	$Δ x m a x Δ n w, m a x$
半圆柱	8.0	3.76×10⁵	0.076 00	1.1×10^-7	8.1×10^-6	170	4.9×10^-3	613	605
半圆柱	16.34	2.97×10⁵	0.076 00	2.6×10^-7	2.0×10^-5	171	1.1×10^-2	545	550
球头	8.0	1.70×10⁵	0.015 00	1.1×10^-7	4.3×10^-6	85	1.8×10^-3	410	419
球头^［17］	8.0	1.70×10⁵	0.015 00	1.1×10^-7	1.3×10^-6	26	5.3×10^-4	410	408
球头	13.24	6.26×10⁴	0.350 00	6.2×10^-7	3.9×10^-5	140	1.1×10^-2	250	282
球头^［26］	13.24	6.26×10⁴	0.350 00	6.2×10^-7	3.5×10^-5	125	1.0×10^-2	250	286
钝头锥^［18］	10.6	2.20×10⁵	0.055 88	4.6×10^-7	4.2×10^-6	20	1.4×10^-3	469	333
升力体^［26］	15.0	1.68×10⁵	0.140 00	9.1×10^-8	8.4×10^-6	206	4.1×10^-3	410	488

Table 1

Fig. 12

Table 2

Collections of flow field parameters for different numerical cases

来流外形	$M a ∞$	$T ∞ / K$	$T t / K$	$T w / K$	$T ∞ / T w$	$T t / T w$	$q s / k W ⋅ m - 2$
半圆柱	8.0	125	1 725.0	294	0.425	5.867	406.2
半圆柱	8.0	125	1 725.0	1 200	0.104	1.438	95.1
半圆柱	16.34	52	2 828.6	294.4	0.177	9.609	527.1
半圆柱	16.34	52	2 828.6	1 000	0.052	2.829	350.4
球头	8.0	64.64	892.0	294	0.220	3.034	554.8
球头	8.0	64.64	892.0	500	0.129	1.784	315.3
球头	13.24	265	9 555.8	294.4	0.900	32.458	911.8
球头	13.24	265	9 555.8	2 000	0.133	4.778	696.2
钝头锥^［18］	10.6	47.3	1 110.2	294.4	0.161	3.771	184.9
升力体^［26］	15.0	250.35	11 516.1	300	0.850	39.117	5 000

Table 2

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Effect of grid strategy on numerical simulation results of aerothermal heating loads over hypersonic blunt bodies

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