List of Tables
Table 1-1 Reference Quantities for the CRM... 9
Table 1-2 Detailed Geometric Data for the CRM Wing ... 11
Table 2-1 Geometric model features ... 19
Table 2-2 Tip section, sketch features ... 26
Table 2-3 Kink section, sketch features ... 27
Table 2-4 Near root sketch features ... 28
Table 2-5 Beyond root sketch features ... 29
Table 3-1 Numerical features of grid cases ... 40
Table 4-1 NTF test 197 run 44 ... 73
Table 4-2 equation system used for derived values ... 76
Table 4-3 Input and derived parameters for Re 5 M and Mach 0.85 ... 77
Table 4-4 Setup parameters for Re 30 M and T 223.25 K ... 81
Table 4-5 CASE 1 aerodynamic coefficient results ... 82
Table 4-6 CASE 2 aerodynamic coefficient results ... 82
Table 4-7 CASE 3 aerodynamic coefficients results ... 83
Table 4-8 ANSYS FLUENT aerodynamic coefficient results ... 83
Table 4-9 Effect of system support and fixed twist angle for Re 5 M ... 87
Table 4-10 Percentage CL error between DPW4 and NTF results, Re 5 M ... 88
Table 4-11 Percentage CL error between NTF and CASE 3 ... 89
Table 4-12 Percentage CD error between NTF and CASE 3 ... 89
Table 5-1 Input and derived parameters ... 91
Table 5-2 Input, derived and reference value for 10000m ... 92
Table 5-3 CL, CD Re 30M Mach 0.85 for curved wing configurations ... 93
Table 5-4 CL, CD Re 50.6M Mach 0.85 for curved wing configurations ... 94
Table 5-5 CL/CD Re 30M Mach 0.85 for curved wing configurations ... 94
Table 5-7 Input,derived and reference values fo h=11300m ... 103 Table 5-8 CL and CD pressure and viscous contributions, for different angle of attack
and M 0.8, 0.85 ... 104 Table 5-9 CL and CD pressure and viscous contributions, for different angle of attack
and M 0.875, 0.9 ... 105 Table 5-10 CD percentage variation for CL 0.5 and M0.8, 0.85, 0.875, 0.9. ... 118 Table 5-11 CL, CD pressure and viscous contributions, for different angle of attack
and M 0.8 and 0.85 ... 147 Table 5-12 CL, CD pressure and viscous contributions, for different angle of attack
and M 0.87 and M 0.9 ... 148 Table 5-13 Wing-only case, L/D for CL=0.5±0.001 for swept and curved planform
shapes with percentage difference ... 159 Table 5-14 Interpolated maximum lift to drag ratio with corresponding lift coefficient
values... 161 Table 5-15 Maximum L/D percentage increase from swept to curved wing ... 161
