Phase II Final Report - NASA's Institute for Advanced Concepts

List of Figures
Figure 3-54: Pressure Contours for a = 11.31 o .......................................................................... 81
Figure 3-55: Velocity Vectors for a = 14.31 o ............................................................................ 82
Figure 3-56: Pressure Contours for a = 14.31 o .......................................................................... 82
Figure 3-57: Velocity Vectors for a = 17.31 o ............................................................................ 83
Figure 3-58: Pressure Contours for a = 17.31 o .......................................................................... 83
Figure 3-59: Airfoil with New, Finer Triangular Mesh ............................................................. 84
Figure 3-60: Cambered, Zero-thickness Airfoil ........................................................................ 84
Figure 3-61: CL Values for the Thick and Thin Airfoils .......................................................... 85
Figure 3-62: Cd Values of the Thick and Thin Airfoils ............................................................ 85
Figure 3-63: Lift Coefficient Variation, a = 8.31 o , Reynolds Number = 9,600 ........................ 87
Figure 3-64: Drag Coefficient Variation, a = 8.31 o , Reynolds Number = 9,600 ...................... 87
Figure 3-65: Velocity Vectors, a = 8.31 o , Reynolds Number = 9,600 ...................................... 88
Figure 3-66: Pressure Contours, a = 8.31 o , Reynolds Number = 9,600 .................................... 88
Figure 3-67: Pressure Contours, a = 45.79 o , Reynolds Number = 5,100, Time = 3.5648 s ...... 89
Figure 3-68: Pressure Contours, a = 45.79 o , Reynolds Number = 5,100, Time = 3.5948 s ...... 89
Figure 3-69: Pressure Contours, a = 45.79 o , Reynolds Number = 5,100, Time = 3.6248 s ...... 90
Figure 3-70: Pressure Contours, a = 45.79 o , Reynolds Number = 5,100, Time = 3.6548 s ...... 90
Figure 3-71: Pressure Contours, a = 45.79 o , Reynolds Number = 5,100, Time = 3.6848 s ...... 91
Figure 3-72: Lift Convergence History. U=1.4 m/s. a = 34.8 o . ................................................. 93
Figure 3-73: Drag Convergence History. U=1.4 m/s. a = 34.8 o ................................................ 93
Figure 3-74: Lift Convergence History. U=14 m/s. a = 34.8 o . .................................................. 94
Figure 3-75: Drag Convergence History. U=14 m/s. a = 34.8 o . ................................................ 94
Figure 3-76: Top View of Entomopter Wing ............................................................................ 95
Figure 3-77: Side View of Entomopter Wing ........................................................................... 95
Figure 3-78: Lift Coefficient for the Oscillating Wing Case ..................................................... 96
Figure 3-79: Drag Coefficient for the Oscillating Wing Case ................................................... 96
Figure 3-80: North American Cicada Forewings and Right Hind Wing ................................... 97
Figure 3-81: Elliptic Wing Modeled After North American Cicada Wing ............................... 97
Figure 3-82: Dimensions Used for Entomopter Wing Mesh Generation .................................. 98
Figure 3-83: Mesh View 1 ......................................................................................................... 99
Figure 3-84: Mesh View 2 ....................................................................................................... 100
Figure 3-85: Mesh View 3 ....................................................................................................... 100
Figure 3-86: Mesh View 4 ....................................................................................................... 100
Figure 3-87: Mesh View 5 ....................................................................................................... 101
Figure 3-88: Mesh View 6 ....................................................................................................... 101
Figure 3-89: Residual Convergence Plot ................................................................................. 102
Figure 3-90: Force Convergence Plot ...................................................................................... 102
Figure 3-91: U Velocity Contours on Symmetry Plane .......................................................... 103
Figure 3-92: U Velocity Contours at Span Location z = -0.26 ................................................ 103
Figure 3-93: U Velocity Contours at Span Location z = -0.5 .................................................. 104
Figure 3-94: Residual Convergence Plot ................................................................................. 105
Figure 3-95: Force Convergence Plot ...................................................................................... 105
Figure 3-96: U Velocity Contours on Symmetry Plane .......................................................... 106
Figure 3-97: U Velocity Contours at Span Location z = -0.26 ................................................ 107
Figure 3-98: U Velocity Contours at Span Location z = -0.5 .................................................. 107
Figure 3-99: Forces (Newtons) Time History for Simulation with Blowing .......................... 109
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