軸対称型スクラムジェットエンジンのbusemann形状空気吸...
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軸対称型スクラムジェットエンジンのBusemann形状空気吸込み口の 軸方向短縮過程におけるマッハ反射形態のヒステリシスの数値解析
小川秀朗(ロイヤルメルボルン工科大学),モルダー・サンヌ(Ryerson大学)
Numerical Analysis of Hysteresis in Mode Transition of Centerline Mach Reflection in Stunted Busemann Intakes
for Axisymmetric Scramjet Engines
Hideaki Ogawa (RMIT University) and Sannu Mölder (Ryerson University)
ABSTRACT Hypersonic air-breathing propulsion, in particular, scramjet (supersonic combustion ramjet) engines, is a promising technology for efficient and economical access-to-space and atmospheric transport. Axisymmetric air intakes based on the Busemann geometry offer appreciable efficiency with maximum total pressure recovery and minimum shock loss, but the inherently long geometry incurs large skin friction drag and structural weight, requiring shortening by some means. Two distinctly different configurations of Mach reflection are found to exist at the centerline for identical inflow conditions and intake lengths in the course of shortening by axial contraction (stunting). Parametric studies with steady and transient numerical simulations are performed to examine the inviscid transient flowfields with variations in the shortening length and freestream Mach number. This paper presents the results and flowfields with focus on the variations of the exit Mach number and temperature as well as intake drag and discusses the hysteresis observed in the stunting and reverse (stretching) process of the Busemann intakes.
1.はじめに
1
SCRAMSPACE 1)
2)3)
2 Busemann
8 Taylor-MaccollEuler
Busemann 4) 2
97%
145第 45 回流体力学講演会 /航空宇宙数値シミュレーション技術シンポジウム 2013 論文集
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5)
43%leading-edge truncation
stunting 2 3 Busemann
6)
3 Busemann 8
6)
.解
30km
1197Pa 226.5K 8
Busemann Taylor-Maccoll5)
Δ L / L full11.2
0.1m Metacomp
CFD++ Euler 2 1
0.0150 6
8)
276201 55,000
. お
8 BusemannΔ L / L full = 0.01
4 2 Δ L / L full = 0.33 4(b)
9)
A Δ L / L full = 0.34 4(c)
BΔ L / L full = 0.44 4(d)
(a) Δ L / L full = 0.23 A
(b) Δ L / L full = 0.33 A
(c) Δ L / L full = 0.34 B
(d) Δ L / L full = 0.44 B
4 Busemann
−3 −2.5 −2 −1.5 −1 −0.5 0
−0.2
0
0.2
x [m]
r [m
]
full BusemannΔL /Lfull =0.2 (truncated)
ΔL /Lfull =0.4 (truncated)
ΔL /Lfull =0.2 (stunted)
ΔL /Lfull =0.4 (stunted)
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5 yΔ L / L fullr z x
5 (a)Δ L / L full = 0.33
Δ L / L full = 0.34
5 (b)
(a)
(b)
5 Busemann
6)
stream thrust 10)
6 (a)4 Δ L / L full = (b) 0.33 (c) 0.34
6 (b)
(a)
(b)
6 Busemann
6)
(a) Δ L / L full = 0.23 B
(b) Δ L / L full = 0.17 B
(c) Δ L / L full = 0.16 A
7 Busemann
200
400
600
800
1000
0
2
4
6
8
0 0.1 0.2 0.3 0.4 0.5
T 2 [K
]
M2
L / Lfull
temperature
Mach number
Δ L / L full = 0.34
0
0.05
0.1
0.15
0.2
0 0.1 0.2 0.3 0.4 0.5
Cd
L / Lfull
Δ L / L full = 0.34
147第 45 回流体力学講演会 /航空宇宙数値シミュレーション技術シンポジウム 2013 論文集
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7
Δ L / L full8
three-shock theory 9 (a)
p3a = p3c θa = θ b+θc
8 Busemann
(a)
(b)
9
9 (b)Polar I
Polar II4 (c) (d) B
9 (b)normal
7 (a) (b)
9 (b) inverted
2
10
B 4 (c) Δ L / L full = 0.34 0.1
12
10 10 (a) 1210 (b)
Boverspeeding
A
8 AΔ L / L full = 0.33
0.111 4 (a) (b)
6 11 (a)
4 11 (b)
2
A
0 0.44/LfullL
0.16 0.17 0.33 0.34
Mach reflection (type A)
Mach r
eflectio
n (type
B)intakeunstart
(full Busemann)
Mac
h st
em h
eigh
t
11, pMaβ
aθ
bβ cθbθ
cβ
22 , pM
pM 3a3a ,
pM 3c3c ,
slipstreamtriple point
01θ
p / p
1
directnormalinverted
slipstream
mechanicalequilibrium
Polar IIPolar I
θcr
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9 (b) 2
9 (a)
11)
(a) 10
(b) 12
10 B8 12
Δ L / L full = 0.34
(a) 6
(b) 4
11 A8 4
Δ L / L full = 0.33
.
8
Busemann
66%
AB
66%
87%A
A B
12 4
.
DECRA (DE120102277) Discovery (RGPIN/298232- 2009)Research Council National Science and Engineering Research Council
149第 45 回流体力学講演会 /航空宇宙数値シミュレーション技術シンポジウム 2013 論文集
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1) Boyce R. R., Tirtey S. C., Brown, L., Creagh, M., and Ogawa, H., “SCRAMSPACE : Scramjet-based Access-to-Space Systems”, AIAA Paper 2011-2297, 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, San Francisco, CA, 2011.
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