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

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Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars Table 3-5: Simulation Conditions (Continued) Free Stream Temperature Solver 210 K Segregated-Implicit, Steady In the CFD analysis, the values of lift and drag coefficients were to be determined. The lift coefficient and the drag coefficient are given by Equations 3-29 and 3-30, respectively. 2 c = L/(0.5 V S) Equation 3-29 l ρ ∞ c = D V S d 2 /(0.5 ρ ∞ ) Equation 3-30 L and D are the lift and drag forces, respectively, p is the density of the fluid, V is the free stream velocity, and S is the wing planform area. All the cases were run for turbulent conditions with the Spalart-Allmaras model and the conditions shown in Table 3-5. After the solutions converged, the C L and c d values were noted. According to the “lifting-line theory,” C L - = 2πα, where α is the angle of attack in radians. The theoretical values of C L obtained from the lifting line theory, and those obtained from the CFD simulations were compared. Figure 3-40 shows the comparison. Figure 3-41: Lift Coefficient vs. Angle of Attack 74 Phase II Final Report
Chapter 3.0 Vehicle Design 3.3 Wing Aerodynamics Figure 3-42: Drag Coefficient vs. Angle of Attack For angles of attack higher than about 100 o , C L plateaus and then decreases, probably indicating the beginning of stall. The velocity vectors show that there is some separation at the trailing edge in the form of a small bubble, but the flow reattaches itself ahead of the trailing edge. The velocity vectors and pressure contours for various angles of attack and the conditions in Table 3-5 are shown in Figures 3- 43 through 3-58. 75
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Planetary Exploration Using Biomime
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Table of Contents Table of Contents
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List of Tables List of Tables Table
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List of Figures List of Figures Fig
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List of Figures Figure 3-54: Pressu
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List of Figures Figure 3-138: Stere
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List of Figures Figure 4-24: Averag
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List of Contributors List of Contri
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Executive Summary Executive Summary
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Chapter 1.0 Introduction Chapter 1.
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Chapter 1.0 Introduction Figure 1-2
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Chapter 1.0 Introduction 1.1 Histor
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Chapter 1.0 Introduction 1.2 Origin
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Chapter 1.0 Introduction 1.3 Missio
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1.3.3.1 Surface Imaging The Entomop
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Chapter 3.0 Vehicle Design 3.3 Wing
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Chapter 3.0 Vehicle Design 3.4 Reci
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Chapter 3.0 Vehicle Design 3.5 Fuel
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Chapter 3.0 Vehicle Design 3.6 Powe
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Chapter 4.0 Entomopter Flight Opera
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Chapter 5.0 Potential Payload Funct
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Chapter 6.0 Media Exposure 6.1 Intr
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Chapter 6.0 Media Exposure 6.3 Onli
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Chapter 6.0 Media Exposure 6.6 Spec
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Chapter 7.0 Conclusion Chapter 7.0
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Appendix A: Mars Atmosphere Data JP
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Appendix A: Mars Atmosphere Data Ge
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Appendix A: Mars Atmosphere Data Ge
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Appendix A: Mars Atmosphere Data Ma
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Appendix B: Sizing Results Appendix
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Appendix B: Sizing Results 30 Wing
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Appendix B: Sizing Results 16 Wing
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Appendix B: Sizing Results Length 0
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Appendix B: Sizing Results Lenght 0
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Appendix C: List of References Appe
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Appendix C: List of References 41.
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Phase II Final Report - NASA's Institute for Advanced Concepts

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