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

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Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars Figure 3-93: U Velocity Contours at Span Location z = -0.5 3.3.1.5.3 Blown Steady State Case In this section, the results for the blown flap case are presented for comparison. The blowing velocity used is 100m/s. Normally the blowing velocity is 4 to 7 times that of the forward velocity, however the low density of the Mars atmosphere may change this rule of thumb. Currently the Mars Entomopter design team has not performed parametric studies to determine the optimum blowing velocity under Mars conditions, however this is a topic for planned follow-on efforts. Once again, in the following figures, “x” is the freestream direction, “y” is the vertical and “z” is the spanwise direction. The wing extends along the negative z direction. Figure 3-94 shows the residual convergence plot for the blown case. As with the unblown steady state case, rapid convergence is reached. Even though the computations were performed in “steady state” mode, the oscillations in the time history are indicative that the flow “wants” to be unsteady. 104 Phase II Final Report
Chapter 3.0 Vehicle Design 3.3 Wing Aerodynamics Figure 3-94: Residual Convergence Plot Figure 3-95 shows the forces in Newtons. The drag does not appear to be affected by the number of computational iterations. The lift, however, is affected. Figure 3-95: Force Convergence Plot 105
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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 2.0 Entomopter Configuratio
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Chapter 3.0 Vehicle Design 3.1 Wing
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Page 117 and 118: 3. Density: 1.40E-2 kg/m 3 4. Press
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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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