Numerical studies on the effect of the key parameter to hypersonic “pitch-up anomaly”

Kang* LI; ZongMin HU; ZongLin JIANG

doi:10.1360/SSPMA2014-00137

SCIENTIA SINICA Physica, Mechanica & Astronomica

SCIENTIA SINICA Physica, Mechanica & Astronomica, Volume 45, Issue 3: 034701(2015) https://doi.org/10.1360/SSPMA2014-00137

Numerical studies on the effect of the key parameter to hypersonic “pitch-up anomaly”

Kang* LI, ZongMin HU, ZongLin JIANG

More info

ReceivedMay 6, 2014
AcceptedAug 11, 2014
PublishedJan 19, 2015

PACS numbers

Previous Table of Contents Next

Rating

Abstract

高温真实气体效应所引起气体比热比g的降低被认为是导致航天飞机“上仰异常”的主要原因. 为详细研究此问题, 本文数值求解了Euler方程, 化学反应源项采用有限速率模型, 考虑了5个组分、17个基元反应. 研究结果表明采用低比热比气体CF₄作为实验气体会导致膨胀区的压力分布与真实气体效应的影响规律不一致, 并不能反映出“上仰异常”现象的本质. 在高温真实气体效应的影响下, 化学反应所带来的影响大于振动激发的影响, 对于y方向半模压力积分Cay来说是3.8倍, 而对于半模力矩积分系数Cam来说是1.7倍. 对比分析表明, 热化学反应导致的比热比分布不均衡是导致“上仰异常”现象出现的根本原因.

Funded by

中国科学院知识创新工程重要方向项目

References

[1] Giuseppe P, Raffaele V. Finite Rate Chemistry Effects on the High Altitude Aerodynamic of An Apollo-Shaped Reentry Capsule. New York: AIAA. 2009, Google Scholar

[2] Park C. Validation of CFD Codes for Real-Gas Regime. New York: AIAA. 1997, Google Scholar

[3] Mundt C. Calculation of Hypersonic, Viscous, Nonequilibrium Flows Around Reentry Bodies Using A Coupled Boundary Layer/Euler Method. New York: AIAA. 1992, Google Scholar

[4] Ernst H H, Claus W. Selected Aerothermodynamic Design Problems of Hypersonic Flight Vehicles. New York: AIAA. 2009, Google Scholar

[5] Compton H R, Schies J R, Suit W T, et al. Stability and control over the supersonic and hypersonic speed range. Conference Paper, NASA Langley, 1983. Google Scholar

[6] Brauckmann G J, Paulson W K. Experimental and computational analysis of the space shuttle orbiter hypersonic pitch-up anomaly. J Spacecr Rockets, 1995, 32(5): 758-764 CrossRef Google Scholar

[7] Muylaert J, Walpot L, Rostand P, et al. Extrapolation from Wind Tunnel to Flight: Shuttle Orbiter Aerodynamics. Technical Report, NASA, 1998. Google Scholar

[8] Griffith B J, Maus J R, Best J T. Explanation of the hypersonic longitudinal stability problem lessons learned. Conference Paper, NASA, 1983. Google Scholar

[9] Romere P O, Whitnah A M. Space shuttle entry longitudinal aerodynamic comparison of flights 1-4 with preflight predictions. Conference Paper, NASA, 1983. Google Scholar

[10] Galloway R L. Real Gas Simulation for the Shuttle Orbiter and Planetary Entry Configurations Including Flight Results. Technical Report, AIAA, 1984. Google Scholar

[11] Gnoffo P A, Gupta R N, Shinn J L. Conservation Equations and Physical Models for Hypersonic Air Flows in Thermal and Chemical Nonequilibrium. Technical Report, NASA, 1989. Google Scholar

[12] Dunn M G, Kang S W. Theoretical and experimental studies of reentry plasmas. Technical Report, NASA, 1973. Google Scholar

[13] Chul P, Wayland G. Nonequilibrium hypersonic aerothermodynamics. Phys Tod, 1991, 42(2): 98 Google Scholar

[14] Millikan R C, White D R. Systematics of vibrational relaxation. J Chem Phys, 1963, 39: 3209-3213 CrossRef Google Scholar

[15] White F A. Viscous Fluid Flow. New York: McGraw-Hill Book Company. 1974, Google Scholar

[16] Seokkwan Y, Antony J. Lower-Upper Symmetric-Gauss-Seidel method for the Euler and Navier-Stokes equations. AIAA J, 1988, 26: 1025-1026 CrossRef Google Scholar

[17] Kim K H, Kim C, Rho O H. Methods for the accurate computations of hypersonic flows I. J Comput Phys, 2001, 174: 38-80 CrossRef Google Scholar

[18] Kim K H, Lee J H, Rho O H. An improvement of AUSM schemes by introducing the pressure-based weight functions. Comput Fluids, 1998, 27(3): 311-346 CrossRef Google Scholar

[19] Keiichi K, Eiji S, Yoshiaki N, et al. Evaluation of Euler flux for hypersonic heating computations. AIAA J, 2010, 48(4): 763-776 CrossRef Google Scholar

[20] Kliche D, Mundt C, Hirschel E H. The hypersonic Mach number independence principle in the case of viscous flow. Shock Waves, 2011, 21: 307-314 CrossRef Google Scholar

[21] Miller J H. Computational Aerothermodynamic Datasets for Hypersonic Heat Transfer on Reentry Vehicles. Technical Report, AIAA, 2005. Google Scholar

[22] Masatoshi K, Hideyuki T, Masahiro T, et al. Comparison of Re-Entry Flow Computations with High Enthalpy Shock Tunnel Experiments. Technical Report, AIAA, 2009. Google Scholar

Click to view Download high-quality image

图1
(网络版彩图)研究模型示意图
Click to view Download high-quality image

图2
(网络版彩图)气动参数Cax, Cay及壁面压力系数分布的网格无关性
Click to view Download high-quality image

图3
(网络版彩图)不同模型下壁面压力分布与实验结果的对比
Click to view Download high-quality image

图4
(网络版彩图)激波前g =1.4和激波层内g =1.35条件下: Cax, Cay和Cam随马赫数的变化
Click to view Download high-quality image

图5
(网络版彩图)Mach=20时Cax, Cay和Cam随激波层内气体比热比的变化: 激波前g为1.4
Click to view Download high-quality image

图6
(网络版彩图)Mach=20时激波层内采用不同气体比热比壁面压力系数的对比: (a) C_p, (b) C_p局部放大图
Click to view Download high-quality image

图7
(网络版彩图)不同气体状态下气动力系数随马赫数的变化, (a) Cax; (b) Cay; (c) Cam; (d) Cax的相对变化量; (e) Cay的相对变化量
Click to view Download high-quality image

图8
(网络版彩图)不同气体状态下壁面无量纲压力分布:Mach=20
Click to view Download high-quality image

图9
(网络版彩图)不同气体状态下激波形状的对比: Mach=20
Click to view Download high-quality image

图10
(网络版彩图)热非平衡气体下激波层内g的分布: Mach=20
Click to view Download high-quality image

图11
(网络版彩图)Cax, Cay, Cam随马赫数的变化, (a) Cax; (b) Cay; (c) Cam; (d) Cax的相对变化量; (e) Cay的相对变化量
Click to view Download high-quality image

图12
(网络版彩图)紧贴激波面后及物面上压力分布的对比: Mach=20
Click to view Download high-quality image

图13
(网络版彩图)紧贴激波面后及物面上气体比热比g的分布: Mach=20
Click to view Download high-quality image

图14
(网络版彩图)Mach=20时不同气体质的量分数分布: (a) O₂, (b) N₂
Click to view Download high-quality image

图15
(网络版彩图)激波层内g的对比: Mach=20
Click to view Download high-quality image

图16
(网络版彩图)q=45°之后流动冻结: (a) Cax; (b) Cay; (c) Cam
Click to view Download high-quality image

图17
(网络版彩图)q=45°之后流动冻结, (a) 激波后及物面上压力分布; (b) 激波层内g的分布

Table 1 Chemical reactions and rate coefficients

Reactions	$k_{f, r}$	$k_{b, r}$	Third body M
$N_{2} + M ? N + N + M$	$4.8 \times 10^{17} T^{? 0.5} \exp (? 1.13 \times 10^{5} / T)$	$2.72 \times 10^{16} T^{? 0.5}$	N₂
	$1.92 \times 10^{17} T^{? 0.5} \exp (? 1.13 \times 10^{5} / T)$	$1.10 \times 10^{16} T^{? 0.5}$	O₂
	$1.92 \times 10^{17} T^{? 0.5} \exp (? 1.13 \times 10^{5} / T)$	$1.10 \times 10^{16} T^{? 0.5}$	NO
	$4.16 \times 10^{22} T^{? 1.5} \exp (? 1.13 \times 10^{5} / T)$	$2.27 \times 10^{21} T^{? 1.5}$	N
	$1.92 \times 10^{17} T^{? 0.5} \exp (? 1.13 \times 10^{5} / T)$	$1.10 \times 10^{16} T^{? 0.5}$	O
$O_{2} + M ? O + O + M$	$7.21 \times 10^{18} T^{? 1.0} \exp (? 5.95 \times 10^{4} / T)$	$6.0 \times 10^{15} T^{? 0.5}$	N₂
	$3.25 \times 10^{19} T^{? 1.0} \exp (? 5.95 \times 10^{4} / T)$	$2.7 \times 10^{16} T^{? 0.5}$	O₂
	$3.61 \times 10^{18} T^{? 1.0} \exp (? 5.95 \times 10^{4} / T)$	$3.0 \times 10^{15} T^{? 0.5}$	NO
	$3.61 \times 10^{18} T^{? 1.0} \exp (? 5.95 \times 10^{4} / T)$	$3.0 \times 10^{15} T^{? 0.5}$	N
	$9.02 \times 10^{19} T^{? 1.0} \exp (? 5.95 \times 10^{4} / T)$	$7.5 \times 10^{16} T^{? 0.5}$	O
$NO + M ? N + O + M$	$3.97 \times 10^{20} T^{? 1.5} \exp (? 7.55 \times 10^{4} / T)$	$1.0 \times 10^{20} T^{? 1.5}$	N₂
	$3.97 \times 10^{20} T^{? 1.5} \exp (? 7.55 \times 10^{4} / T)$	$1.0 \times 10^{20} T^{? 1.5}$	O₂
	$7.94 \times 10^{20} T^{? 1.5} \exp (? 7.55 \times 10^{4} / T)$	$2.0 \times 10^{21} T^{? 1.5}$	NO
	$7.94 \times 10^{20} T^{? 1.5} \exp (? 7.55 \times 10^{4} / T)$	$2.0 \times 10^{21} T^{? 1.5}$	N
	$7.94 \times 10^{20} T^{? 1.5} \exp (? 7.55 \times 10^{4} / T)$	$2.0 \times 10^{21} T^{? 1.5}$	O
$N_{2} + O ? NO + N$	$6.74 \times 10^{13} \exp (? 3.8 \times 10^{4} / T)$	$1.56 \times 10^{13}$
$NO + O ? O_{2} + N$	$3.18 \times 10^{9} T^{? 1.0} \exp (? 1.97 \times 10^{4} / T)$	$1.3 \times 10^{10} T^{? 1.0} \times \exp (? 3.58 \times 10^{3} / T)$

表2 网格无关性研究

Grid change in I direction

Grid change in J direction

Grid case

Mx

Ny

Grid case

Mx

Ny

1

201

260

1

361

00

2

251

260

2

361

50

3

301

260

3

361

00

4

401

260

4

361

00

1

Citations
0

Altmetric
Article metrics

Email
Export


47.11.Bc	Finite difference methods
47.70.Fw	Chemically reactive flows (see also 83.80.Jx-in rheology)
47.70.Nd	Nonequilibrium gas dynamics
47.85.Gj	Aerodynamic

Numerical studies on the effect of the key parameter to hypersonic “pitch-up anomaly”

Abstract

Funded by

References

1

0

Interesting search

Top 5Related Articles

Grid change in I direction			Grid change in J direction
Grid case	Mx	Ny	Grid case	Mx	Ny
1	201	260	1	361	00
2	251	260	2	361	50
3	301	260	3	361	00
4	401	260	4	361	00