Index of Figures

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Index of Figures

Figure 1-1 Shock wave development on a 2D airfoil with increasing Mach numbers .. 3

Figure 1-2 CRM planform and dimensions ... 10

Figure 1-3 CRM semimodel front view ... 12

Figure 1-4 Side-view of the airfoil stack as rigged in the fuselage reference plane. ... 12

Figure 1-5 Non-dimensional maximum thickness to chord ratio across the wing ... 13

Figure 1-6 Max camber distribution of the CRM wing ... 13

Figure 1-7 Twist distribution of the CRM wing ... 14

Figure 1-8 CRM Lateral view of the fuselage ... 14

Figure 2-1 CRM airfoils obtained by intersection with cross-planes ... 16

Figure 2-2 Wing airfoil copies and cross-planes for zero values of translation ... 17

Figure 2-3 Wing structure composed by sections and guidelines ... 17

Figure 2-4 Curved wing coordinate system and polynomial lawparameters ... 18

Figure 2-5 CRM planform view ... 20

Figure 2-6 CRM and 6 m 53° curved planform wing comparison ... 21

Figure 2-7 CRM and 6 m 53°curved planform wing comparison ... 21

Figure 2-8 CRM and 6.4 m 59° curved planform wing comparison ... 22

Figure 2-9 CRM and 6.4 m 59° curved planform wing airfoils comparison ... 22

Figure 2-10 CRM and 3 m 45° curved planform wing comparison ... 23

Figure 2-11 CRM and 3 m 45° curved planform wing airfoils comparison ... 23

Figure 2-12 Curved planform wing, leading edge comparison ... 24

Figure 2-13 Curved planform wings, Leading edge sweep angle comparison ... 24

Figure 2-14 Tip section, sketch of the wing profile, construction lines ... 25

Figure 2-15 Tip 3D profiles defining closed regions ... 26

Figure 2-16 Kink section, sketch of the wing profile, construction lines ... 27

Figure 2-17 Near root section, sketch of the wing profile, construction lines ... 28

Figure 2-18 Beyond root section, sketch of the wing profile, construction lines ... 29

Figure 2-19 Control volumes around the wing... 30

Figure 2-20 Control volumes kink-tip and kink -root ... 30

Figure 2-21 Wing control volumes, upper view ... 31

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Figure 2-23 Tip pod outer side view ... 32

Figure 2-24 Tip pod inner side view ... 32

Figure 2-25 Fuselage control volume and building sections ... 33

Figure 2-26 Control volumes for swept wing configuration ... 33

Figure 2-27 Control volumes for curved wing configuration ... 33

Figure 2-28 Control intersections ... 34

Figure 2-29 Far field dimensions in mm ... 35

Figure 2-30 Far field surface ... 35

Figure 3-1 H-grid outer macro-block configuration, far-field rectangular faces ... 37

Figure 3-2 H-grid outer macro-block, far-field with rectangular faces: side view ... 37

Figure 3-3 H-grid plus O-grid configuration with semispherical far-field ... 38

Figure 3-4 H-grid plus O-grid configuration with semispherical far-field: side view . 38 Figure 3-5 Inner macro-block, the sheath... 39

Figure 3-6 Sheath blocks broken view ... 39

Figure 3-7 Wing O-grid blocks from root to tip ... 39

Figure 3-8 CASE 1 far-field blocks view from positive y direction ... 41

Figure 3-9 CASE 1 far-field blocks edges oblique view ... 41

Figure 3-10 CASE 1 mesh shell distribution in the far-field faces, isometric view ... 42

Figure 3-11 CASE 1 shell distribution in the symmetry plane ... 42

Figure 3-12 Fuselage blocking CASE 1. ... 43

Figure 3-13 Fuselage mesh shell. ... 43

Figure 3-14 Fuselage nose mesh shell. ... 43

Figure 3-15 Fuselage tail mesh shell ... 44

Figure 3-16 Fuselage fairing mesh shell. ... 44

Figure 3-17 Interconnecting belt isolated ... 45

Figure 3-18 Interconnecting belt leading edge view with wing and fuselage fairing .. 45

Figure 3-19 Interconnecting belt trailing edge view with wing and fuselage fairing .. 45

Figure 3-20 Interconnecting belt blocking on leading side ... 46

Figure 3-21 Interconnecting belt blocking edges on trailing edge ... 46

Figure 3-22 Upper view of wing splits ... 47

Figure 3-23 Tip trailing edge face wiew of O-grid shells ... 47

Figure 3-24 Tip trailing edge detail of the O-grid type blocking ... 48

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Figure 3-26 O-grid leaving the tip trailing edge through the far-field boundary ... 48

Figure 3-27 Tip mesh shells, side view ... 49

Figure 3-28 Tip sheath blocking... 49

Figure 3-29 Tip trailing side ... 50

Figure 3-30 Tip leading side... 50

Figure 3-31 Symmetry shell CASE 1. ... 51

Figure 3-32 Symmetry shell CASE 2 ... 51

Figure 3-33 CASE 2 fuselage blocking ... 52

Figure 3-34 CASE 2 cockpit mesh shell ... 52

Figure 3-35 CASE 3 intermediate macroblock view ... 53

Figure 3-36 CASE 3 broken view of the blocking ... 54

Figure 3-37 CASE 3 symmetry plane mesh shell ... 54

Figure 3-38 Legend of variables in the O-grid wing sections along x and z direction 60 Figure 3-39 Legend of variables in the O-grid fuselage sections along x direction. .... 60

Figure 3-40 Automation procedure flow chart ... 67

Figure 4-1 CRM wind tunnel model ... 69

Figure 4-2 NTF wind tunnel view with CRM and its support structure ... 70

Figure 4-3 CRM model frontal view ... 70

Figure 4-4 CL-α curves for Re 5 M, SST turbulent model ... 78

Figure 4-5 CD-α curves for Re 5 M, SST turbulent model ... 78

Figure 4-6 CFD simulations with SA and SST turbulent models ... 79

Figure 4-7 CL-α chart for M 0.85, Re 30 M, different meshes and NTF data ... 84

Figure 4-8 CD-α chart for M 0.85, Re 30 M, different meshes and NTF data ... 84

Figure 4-9 CL/CD-α for M 0.85, Re 30 M, different CFD and NTF data ... 85

Figure 4-10 CL-CD chart for Re 30 M, different meshes and NTF data ... 85

Figure 4-11 Summary of DPW 4 simulations in terms of CL alpha chart ... 86

Figure 5-1 CL-α Re 30 M ... 95

Figure 5-2 CD-α Re 30 M ... 95

Figure 5-3 CL-CD Re 30 M ... 96

Figure 5-4 L/D-α Re 30 M ... 96

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Figure 5-6 CL-α Re 50.6M ... 97

Figure 5-7 CD-α Re 50.6M ... 98

Figure 5-8 CL-CD Re 50.6 M ... 98

Figure 5-9 L/D-α Re 30 M ... 99

Figure 5-10 L/D-CL Re 50.6 M ... 99

Figure 5-11 CRM swept geometry ... 101

Figure 5-12 3000 45° curved geometry ... 101

Figure 5-13 Comparison between CRM swept wing and 3000 45° ... 101

Figure 5-14 CASE 3 surface mesh for swept configuration... 102

Figure 5-15 Figure 5-16 CASE 3 surface mesh for curved configuration ... 102

Figure 5-17 CL-α curve for Mach number 0.8, at a flight altitude h 11300 meters ... 106

Figure 5-18 CL-α curve for Mach number 0.85, at a flight altitude h 11300 meters . 106 Figure 5-19 CL-α curve for Mach number 0.875, at a flight altitude h 11300 meters107 Figure 5-20 CL-α curve for Mach number 0.9, at a flight altitude h 11300 meters ... 107

Figure 5-21 CD-α curve for Mach number 0.8, at a flight altitude h 11300 meters .. 108

Figure 5-22 CD-α curve for Mach number 0.85, at a flight altitude h 11300 meters 108 Figure 5-23 CD-α curve for Mach number 0.875, at a flight altitude h 11300 meters ... 109

Figure 5-24 CD-α curve for Mach number 0.9, at a flight altitude h 11300 meters .. 109

Figure 5-25 Polar CL-CD curve for Mach number 0.8, at a flight altitude h 11300 meters ... 110

Figure 5-27 Polar CL-CD curve for Mach number 0.875, at a flight altitude h 11300 meters ... 111

Figure 5-29 L/D-α curve for Mach number 0.8, at a flight altitude h 11300 meters .. 112

Figure 5-30 L/D-α curve for Mach number 0.85, at a flight altitude h 11300 meters 112 Figure 5-31 L/D-α curve for Mach number 0.875, at a flight altitude h 11300 meters ... 113

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Figure 5-33 L/D-CL curve for Mach number 0.8, at a flight altitude h 11300 meters

... 115

Figure 5-34 L/D-CL curve for Mach number 0.85, at a flight altitude h 11300 meters ... 115

Figure 5-38 CD-M curve for varying Mach numbers, at a flight altitude h 11300 meters ... 118

Figure 5-39 Cp profile for M 0.8 15%b ... 120

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Figure 5-67 sonic region, swept wing M 0.8 frontal view ... 136

Figure 5-68 sonic region, curved wing M 0.8 frontal view ... 137

Figure 5-69 sonic region, swept wing M 0.8, oblique view ... 137

Figure 5-70 sonic region, curved wing M 0.8, oblique view ... 138

Figure 5-73 sonic region, swept wing M 0.85 M 0.85 oblique view ... 139

Figure 5-74 sonic region, curved wing M 0.85 oblique view ... 140

Figure 5-77 sonic region, swept wing M 0.875 oblique view ... 141

Figure 5-81 sonic region, swept wing M 0.9 oblique view ... 143

Figure 5-83 CL-α curves, wing-only and wing-body models for swept and curved planforms, M=0.8 ... 149

Figure 5-84 CL-α, wing-only and wing-body models for swept and curved planforms, M=0.85 ... 149

Figure 5-87 CD-α curves, wing-only and wing-body models for swept and curved planforms, M=0.8 ... 151

Figure 5-88 CD-α, wing-only and wing-body models for swept and curved planforms, M=0.85 ... 151

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Figure 5-89 CD-α, wing-only and wing-body models for swept and curved planforms,

M=0.875 ... 152

Figure 5-90 CD-α, wing-only and wing-body models for swept and curved planforms, M=0.9 ... 152

Figure 5-91 Polar CL-CD curves, wing-only and wing-body models for swept and curved planforms, M=0.8 ... 153

Figure 5-92 Polar CL-CD, wing-only and wing-body models for swept and curved planforms, M=0.85 ... 153

Figure 5-95 L/D-α, wing-only and wing-body models for swept and curved planforms, M=0.8 ... 155

Figure 5-99 L/D -CL, wing-only and wing-body models for swept and curved planforms, M=0.8 ... 157

Figure 5-100 L/D-CL, wing-only and wing-body models for swept and curved planforms, M=0.85 ... 157

Figure 5-101 L/D-CL, Swept and curved planforms cases for alone and wing-body models, M=0.875 ... 158

Figure 5-102 L/D-CL, Swept and curved planforms cases for alone and wing-body models, M=0.9 ... 158

Figure A-1 EFD and CFD Cp for Re 30 M Mach 0.85 η 0.131 ... 169