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

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Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars The flow conditions used in the WIND simulations represented the Mars environment. These conditions are shown in the list above. Qualitative results from these simulations can be seen in Figures 3-30 through 3-35. Figure 3-30 shows the complexity of the flowfield and dynamic stall vortex using massless particles released ahead of the wing. Figure 3-32 shows the outline of the wing (black lines) with a Mach number cut and velocity vectors depicted near the wing tip. A dynamic stall vortex and flow ejection off the trailing edge can be seen. Figure 3-33 shows the dynamic stall vortex using streamlines. Figures 3-34 and 3-35 show the airfoil surface and LEV development. Animation of time-dependent calculations showed the familiar repeated shedding of dynamic stall vortices from the leading edge across the airfoil. This interaction of vortices with the upper wing surface at this Reynolds number results in higher lift coefficients over the case without oscillation (a static airfoil such as on a fixed wing airplane). Quantitative results were also obtained, as shown in Figures 3-36 and 3-37. Figure 3-36 shows the drag coefficient vs. time with blowing and oscillation. Figure 3-37 shows the lift coefficient vs. time with blowing and oscillation. Similar lift and drag results were found for the case without blowing. It is expected that blowing should increase circulation above and beyond the contributions to oscillation alone. However, in all figures except Figure 3-31, the blowing was ejected tangential to the top wing surface (which is essentially horizontal). However, blowing horizontally off of the flat trailing edge just acts as a jet of air, and does not add to circulation of the airfoil. Thus, the WIND flapping (or oscillating) results show similar lift and drag for the case with and without blowing when a zero-degree jet angle is used. This combination of blowing and flapping gave a maximum lift coefficient of 4 and maximum drag coefficient of 0.85 at a total pressure ratio of 1.27. Figure 3-38 shows the pressure contour field for the case with blowing (left) and no blowing (right). As a side study, a few calculations were completed with mass ejection at a 30 deg angle down (Figure 3-31) from the bottom rear of the airfoil (jet flap), in hopes that it would help induce circulation over the top of the airfoil. It turned out it did not, agreeing with the limited lift augementation benefit of the jet flap concept seen in literature. It should be mentioned that the high lift augmentation characteristics of blowing over a curved trailing edge [81] which we envision for use on this vehicle have not yet been investigated here. 68 Phase II Final Report
Chapter 3.0 Vehicle Design 3.3 Wing Aerodynamics Figure 3-30: Dynamic Stall Vortex Highlighted by Massless Particles Figure 3-31: Cambered Airfoil Surface with 30 o Ejection from the Bottom Rear of the Airfoil Figure 3-32: Wing Outline and Trailing Edge Mass Ejection Used for Circulation Control Figure 3-33: Dynamic Stall Vortex Highlighted Using Streamlines 69
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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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Chapter 1.0 Introduction 1.3 Missio
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Chapter 3.0 Vehicle Design 3.3 Wing
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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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