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

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Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars expensive to simulate on Earth. Additionally, the fundamental basis of the Navier-Stokes equations (Reynolds-averaged) tightly couples CFD to physics. The ability to acquire the data from the time history of unsteady forces and vortex formation on the wing is extremely important and has been demonstrated in this report. The Entomopter vehicle design hinges on whether or not the wings can generate sufficient lift and have an acceptable lift-to-drag ratio. This section will address computations with the CFD codes WIND and FLUENT, as well as codes from Metacomp Technologies, Inc., presented in chronological order. Three-dimensional cases with blowing were simulated initially using WIND to determine if aerodynamic performance can be enhanced by surface blowing. Cases showing the effect of blowing tangential to the trailing edge surface are presented. Animations of the resulting flow fields show the effect of blowing. A major part of the effort at the University of Missouri-Rolla (UMR) with FLUENT has been to design the airfoil section and the 3D planform to mimic the aerodynamic attributes of a typical insect wing. A cicada wing was analyzed for its aerodynamic parameters, such as camber, thickness, planform, structural attributes, and role of the hind wing. Extensive literature review was conducted on the aerodynamic aspects of insect flight and the current status of insect-derived MAV design. A series of two-dimensional studies was conducted using FLUENT to optimize airfoil section parameters, such as thickness and camber, and to establish leading edge vortex (LEV) behavior. Reynolds number was varied by a factor of 10, and the resulting flow fields have been analyzed. A small thickness, cambered three-dimensional wing was designed for the work in progress on flapping wing simulations. Understanding low Reynolds unsteady aerodynamics and controlling wing kinematics during the stroke cycle have been identified as key topics for the continuing Entomopter CFD work. 3.3.1.2 Entomopter Wing CFD Analysis: WIND Preliminary CFD calculations were conducted with WIND Version 3 Code [283], a product of the NPARC Alliance, a partnership between NASA Glenn Research Center (GRC) and Arnold Engineering Development Center (AEDC) dedicated to the establishment of a national, applications-oriented flow-simulation capability. WIND solves the Reynolds-averaged Navier-Stokes equations, along with supporting equation sets governing turbulent and chemically reactive flows. Calculations with WIND were completed early in the project to get some idea of the complexity and physics associated with a sinusoidally oscillating airfoil with tangential blowing. Although the sinusoidal flapping motion did not physically represent the actual motion of the Entomopter wing, purely sinusoidal flapping runs were important in understanding basic vortex creation and convection over the airfoil, which ultimately drives the aerodynamics and wing lift. Both steady and unsteady computations with an oscillating inflow and blowing (mass ejection at the wing tips) were completed to assess the code's ability to handle this very demanding flow field, which includes a very low Mach number inflow, with sinusoidal oscillation to simulate flapping motion, and mass ejection on the outer wing panels to simulate blowing. Blowing is used to entrain lower energy boundary-layer air and reenergize it with higher energy air, decreasing the tendency for the flow to separate and thereby increasing circulation. This, along 66 Phase II Final Report
Chapter 3.0 Vehicle Design 3.3 Wing Aerodynamics with vortex action, leads to very high lift coefficients despite the very low dynamic pressure of the Mars atmosphere. The final computational grid, created with GRIDGEN [109] software, consisting of 495,824 points (fairly coarse), is shown in Figure 3-28. Details of the grid on the wing surface can be seen in Figure 3-29. The wing is an untapered, unswept, viscous, cambered flat plate representing a generic low speed airfoil. The Navier-Stokes equations were solved at the grid points, simulating the flow over the Entomopter wing. Figure 3-28: Computational Grid Figure 3-29: Surface Grid WIND Version 3 Simulation Conditions: • Mars atmosphere: Treated as 100% CO 2 • Mach number = 0.09 (~30 mph) • Total pressure = 0.11 psi • Total temperature = -207 o F (252 Rankine) • angle of attack = 5 o • Laminar viscosity = 2.235e-7 slug/foot-second • Oscillation rate, amplitude: 15 cycles/second, 20 o • Blowing parameters: Pressure = 0.14 psi, temperature = 700 o R • Spalart-Allmaras turbulence model • Reynolds number: About 6,000 • Wing span = 39.4" • Wing chord = 6.38 inches (constant chord) • Blowing region area = 10.74 in 2 (2.1% of wetted area) 67
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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 3.0 Vehicle Design 3.3 Wing
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Chapter 3.0 Vehicle Design 3.5 Fuel
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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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