LES of shock wave / turbulent boundary layer interaction

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Nomenclature Roman symbols a C f = h E F E ,F S G G T G E ,G S H E ,H S J k M = U a p Pr q x ,q y ,q z Q N Re τ w 1 2 ρ ∞U 2 ∞ Re δ = ρ∗ ∞U ∗ ∞δ ∗ µ ∗ ∞ speed of sound skin-friction coefficient compression-decompression corner height total energy convective and diffusive fluxes in streamwise direction filter kernel, Görtler number Görtler number for turbulent flow convective and diffusive fluxes in spanwise direction convective and diffusive fluxes in wall-normal direction determinant of Jacobian matrix specific-heats ratio Mach number static pressure Prandtl number heat fluxes in respective direction deconvolution operator Reynolds number Reynolds number based on boundary layer thickness Re δ1 = ρ∗ ∞U ∗ ∞δ ∗ 1 µ ∗ ∞ Reynolds number based on displacement thickness Re θ = ρ∗ ∞U ∗ ∞δ ∗ 2 µ ∗ ∞ Re δ2 = ρ∗ ∞U ∗ ∞δ ∗ 2 µ ∗ w t Reynolds number based on momentum thickness Reynolds number based on momentum thickness and wall viscosity time
Page 1: Technische Universität München Le
Page 5 and 6: Contents Contents List of figures L
Page 7 and 8: List of Figures 1.1 Examples of can
Page 9: List of Tables 1.1 Streamwise dista
Page 13: Nomenclature XI Subscripts • S
Page 17 and 18: Chapter 1 Introduction Design of ne
Page 19 and 20: 3 shock shock M > 1 M > 1 (a) (b) s
Page 21 and 22: 5 Figure 1.2: Essential flow phenom
Page 23 and 24: 7 et al., 1983; Zheltovodov & Yakov
Page 25 and 26: 9 under free-stream conditions M
Page 27 and 28: in terms of surface pressure, skin
Page 29 and 30: 13 eling issues, the main reason fo
Page 31: eferred to as “higher-Reynolds-nu
Page 34 and 35: Simulation method (a) (b) Figure 2.
Page 36 and 37: Simulation method in the respective
Page 38 and 39: Simulation method Herêdenotes a s
Page 40 and 41: Simulation method exact filtered sh
Page 43 and 44: Chapter 3 Flat plate boundary layer
Page 45 and 46: 29 directions are 45.8 and 17.7. He
Page 47 and 48: 31 Figure 3.2: Instantaneous z−vo
Page 49 and 50: 33 extended to the compressible cas
Page 51 and 52: 35 comparison can be considered as
Page 53 and 54: 37 time by a 3rd-order Neville-Aitk
Page 55 and 56: Chapter 4 Compression corner flow T
Page 57 and 58: 41 Figure 4.1: Compression corner m
Page 59 and 60: 43 ber is comparably large, the for
Page 61 and 62:
45 where we show the distribution o
Page 63 and 64:
47 C f E1 2.0×10 -3 1.6×10 -3 2.0
Page 65 and 66:
49 C f 3×10 -3 x 1 2×10 -3 (a) 1
Page 67 and 68:
51 in the considered range (only at
Page 69 and 70:
for this situation. Here R = d2 z s
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55 streamwise vortices with estimat
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57 it reaches its maximum upstream
Page 75 and 76:
59 5 4 3 1 0.5 0 -4 -2 0 2 4 1 0.5
Page 77 and 78:
61 0.2 σp w p w 0.1 I S P R (a) .
Page 79 and 80:
63 the instantaneous flow also. Thi
Page 81 and 82:
Figure 4.17: Three-dimensional flow
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67 second stem of the λ-shock. We
Page 85 and 86:
efore, aside from direct interactio
Page 87 and 88:
71 4 1 2 3 4 5 6 7 8 9 3 x 3 〈ρu
Page 89 and 90:
73 (a) (b) Figure 4.22: Reynolds no
Page 91 and 92:
75 1 15 0.8 x 3 0.6 〈U〉 + VD 10
Page 93 and 94:
Chapter 5 Compression-decompression
Page 95 and 96:
79 (a) (b) (c) Figure 5.1: Instanta
Page 97 and 98:
81 3 0 0.5 1 E1 0 0.5 1 0 0.5 1 0 0
Page 99 and 100:
83 C f E1 2.0×10 -3 1.6×10 -3 E2
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85 boundary layer show a good agree
Page 103 and 104:
87 (V) is the turbulent diffusion
Page 105:
89 0.003 0.002 0.001 (c) 0 -0.001 -
Page 109:
Appendix A Summary of flat-plate bo
Page 112 and 113:
Hunt & Nixon (1995) N/A N/A Adams (
Page 114 and 115:
Reference Stolz et al. Kannepalli E
Page 117 and 118:
Appendix C Computational details Fo
Page 119 and 120:
Bibliography Adams, E. W. & Johnsto
Page 121 and 122:
105 Chapman, D., Kuehn, D. & Larson
Page 123 and 124:
107 Hunt, D. L. & Nixon, D. 1995 A
Page 125 and 126:
109 Loginov, M. S., Adams, N. A. &
Page 127 and 128:
111 Rizzetta, D. P., Visbal, M. R.
Page 129 and 130:
113 Urbin, G., Knight, D. & Zheltov
Page 131:
115 prospects in supersonic turbule
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